Pre-cooling heat exchanger for aircraft and aircraft

Abstract

The invention relates to the technical field of aircrafts, in particular to a precooling heat exchanger for an aircraft and the aircraft.The precooling heat exchanger comprises a heat exchange core, the heat exchange core comprises at least three partition plates which are stacked and arranged at intervals, and an air flow channel is formed between every two adjacent partition plates; wherein a heat exchange working medium runner is formed between the other two adjacent partition plates, the heat exchange core body sequentially comprises a high-temperature section area, a medium-temperature section area and a low-temperature section area in the first direction, the partition plates of the high-temperature section area and the heat exchange fins are made of nickel base alloy materials, the partition plates of the medium-temperature section area and the heat exchange fins are made of titanium aluminum alloy materials, and the partition plates of the low-temperature section area are made of titanium aluminum alloy materials. The partition plates and the heat exchange fins of the low-temperature section area are all made of aluminum alloy materials. The partition plate of the high-temperature section area is connected with the partition plate of the medium-temperature section area through a flexible expansion compensation piece, and the partition plate of the medium-temperature section area is connected with the partition plate of the low-temperature section area through a flexible expansion compensation piece; and in the second direction, part of the plate sections of the partition plates form sawtooth-shaped plate sections, so that the risk of deformation and failure of the heat exchanger is reduced, and the light weight of the heat exchange core body is achieved.

Description

TECHNICAL FIELD

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

[0002] The high speed of aircraft has extremely important military and civilian values, and the aerodynamic heating effect generated by the aircraft when flying at high speed restricts the flight limit of the aircraft.

[0003] A turbine engine is an important component of an aircraft, which is used to provide flight power for the aircraft. In order to improve the flight speed of the turbine engine, the related technology cools the ram air through a pre-cooling heat exchanger, so that the temperature of the inlet air flow is reduced, in order to offset the temperature rise caused by the aerodynamic heating effect when flying at high speed to a certain extent. However, the pre-cooling heat exchanger of the related technology is prone to deformation at high temperature, which causes damage and even failure of the pre-cooling heat exchanger. SUMMARY

[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 aircraft and an aircraft, which can reduce the risk of deformation and failure of the pre-cooling heat exchanger to a certain extent.

[0005] In a first aspect, the present disclosure provides a pre-cooling heat exchanger for aircraft, comprising a heat exchange core, the heat exchange core comprising at least three stacked and spaced apart baffles, among every three adjacent baffles, two adjacent baffles form an air flow channel, and the other two adjacent baffles form a heat exchange working medium flow channel for the flow of heat exchange working medium, the air flow channel is arranged along a first direction of the baffle, the air flow channel is provided with heat exchange fins, and the heat exchange working medium flow channel is arranged along a second direction of the baffle; the first direction and the second direction are perpendicular to each other; In the first direction, the heat exchange core comprises a high-temperature section, a medium-temperature section and a low-temperature section in sequence, the baffles and heat exchange fins in the high-temperature section are made of nickel-based alloy material, the baffles and heat exchange fins in the medium-temperature section are made of titanium-aluminum alloy material, and the baffles and heat exchange fins in the low-temperature section are made of aluminum alloy material; The baffles between the high-temperature section and the medium-temperature section and the baffles between the medium-temperature section and the low-temperature section are connected by flexible expansion compensation members; In the second direction, part of the baffle section is formed into a zigzag baffle section.

[0006] Optionally, the flexible expansion compensation member is a curved structure extending along the first direction, the curved structure comprises at least one U-shaped section, and the U-shaped section is recessed towards the inner cavity direction of the air flow channel.

[0007] Optionally, a height of the flexible expansion compensation member is not greater than half of a height of the air flow channel in a height direction of the heat exchange core. Optionally, a width dimension of the U-shaped section in the first direction ranges from 20 mm to 30 mm.

[0008] Optionally, the flexible expansion compensation member is a curved alloy foil sheet formed by pressing an alloy foil.

[0009] Optionally, both sides of the air flow channel in the first direction and both sides of the heat exchange working medium flow channel in the second direction are provided with a sealing strip. The sealing strip includes a body layer and an elastic layer outside the body layer.

[0010] Optionally, the body layer is a nickel-based alloy foil layer, and the elastic layer is a silicone rubber layer.

[0011] Optionally, a sawtooth angle of the sawtooth-shaped plate section ranges from 60° to 90°.

[0012] Optionally, in the first direction, a length ratio of the high-temperature section, the medium-temperature section, and the low-temperature section is 2:3:3.

[0013] Optionally, the heat exchange working medium is a liquid metal.

[0014] In a second aspect, the present disclosure provides an aircraft including an engine and the aircraft pre-cooling heat exchanger as described above. The aircraft pre-cooling heat exchanger is located on an air inlet side of the engine.

[0015] The aircraft pre-cooling heat exchanger and the aircraft provided by the present disclosure achieve a cross-flow plate-fin heat exchanger by making the heat exchange core of the pre-cooling heat exchanger include at least three stacked and spaced-apart baffles, making two adjacent baffles among every three adjacent baffles form an air flow channel, making the other two adjacent baffles form a heat exchange working medium flow channel for the heat exchange working medium to flow, arranging heat exchange fins in the air flow channel, and vertically arranging the air flow channel and the heat exchange working medium flow channel, thereby improving the heat exchange efficiency of the ram air.

[0016] By sequentially comprising the high-temperature section area, the medium-temperature section area and the low-temperature section area along the first direction, the baffle and the heat exchange fin in the high-temperature section area are made of nickel-based alloy material, the high-temperature strength, the oxidation resistance and the corrosion resistance of the baffle and the heat exchange fin in the high-temperature section area are improved, the baffle and the heat exchange fin in the high-temperature section area can maintain structural stability under extremely high temperature; the baffle and the heat exchange fin in the medium-temperature section area are made of titanium-aluminum alloy material, the high specific strength, the high specific stiffness and the heat resistance of the baffle and the heat exchange fin in the medium-temperature section area are improved, and the weight of the heat exchange core is greatly reduced; the baffle and the heat exchange fin in the low-temperature section area are made of aluminum alloy material, the heat conduction performance and the stability of the baffle and the heat exchange fin in the low-temperature section area are improved, and the weight of the heat exchange core is greatly reduced.

[0017] That is, by matching the corresponding materials for different temperature section areas of the heat exchange core, the material of the baffle and the fin in each section area is better matched with the temperature of the corresponding section area under high temperature, avoiding the mismatch of the thermal expansion coefficient caused by using the same single material in different temperature section areas, and thus avoiding the deformation, cracking and other conditions of the baffle of the heat exchange core, and the lightweight of the heat exchange core is also achieved, so that the pre-cooling heat exchanger meets the strict requirements of airborne equipment on weight.

[0018] Meanwhile, the baffle of the high-temperature section area and the baffle of the medium-temperature section area, and the baffle of the medium-temperature section area and the baffle of the low-temperature section area are connected by flexible expansion compensation members, effectively relieving the stress concentration at the interface of different materials, reducing the stress concentration coefficient, avoiding deformation and cracking, and thus avoiding deformation and damage of the heat exchanger.

[0019] Moreover, along the second direction, part of the baffle is formed into a zigzag plate section, so that the baffle can effectively absorb the thermal expansion of the metal baffle under high temperature by the elastic deformation of the material itself, effectively solving the macroscopic expansion problem of the metal material from cold state to hot state, reducing the stress concentration coefficient, improving the thermal fatigue life of the heat exchanger, avoiding damage of the heat exchanger, and ensuring stable operation of the pre-cooling heat exchanger under high temperature working conditions.

[0020] It is to be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further explanation of the subject technology claimed. BRIEF DESCRIPTION OF DRAWINGS

[0021] The foregoing and other objects, features and advantages of the present disclosure will become more apparent from the following detailed description, which proceeds with reference to the accompanying drawings. The accompanying drawings are provided to assist in understanding the present disclosure and constitute a part of the specification. The drawings together with the present disclosure are used to explain the present disclosure and do not constitute a limitation on the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0022] Figure 1 Structure diagram of a precooled heat exchanger, an engine and a propulsion channel for an aircraft according to an embodiment of the present disclosure; Figure 2 Structure diagram of a heat exchange core according to an embodiment of the present disclosure; Figure 3 Structure diagram of a partitioned heat exchange core according to an embodiment of the present disclosure; Figure 4 Structure diagram of a baffle, a seal and a flexible expansion compensation member of a heat exchange core according to an embodiment of the present disclosure; Figure 5 Local structure diagram of a flexible expansion compensation member and a baffle according to an embodiment of the present disclosure; Figure 6 Local structure diagram of a heat exchange core according to an embodiment of the present disclosure; Figure 7 Sectional structure diagram of a seal according to an embodiment of the present disclosure.

[0023] Wherein, 100, a precooled heat exchanger; 10, a heat exchange core; 1, a baffle; 11, an air flow channel; 111, a heat exchange fin; 12, a heat exchange working medium flow channel; 13, a high-temperature section; 14, a medium-temperature section; 15, a low-temperature section; 16, a sawtooth plate section; 2, a flexible expansion compensation member; 21, a U-shaped section; 3, a seal; 31, a body layer; 32, an elastic layer; 200, a propulsion channel; 300, an engine; 400, a tail nozzle. DETAILED DESCRIPTION

[0024] In order to make the objectives, technical solutions and advantages of the present disclosure more obvious, the following will describe the example embodiments according to the present disclosure in detail with reference to the drawings. Obviously, the described embodiments are only some of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the example embodiments described herein.

[0025] The term “comprising” and variations thereof as used herein are open-ended, that is, “including but not limited to”. The term “based on” is “based, at least in part, 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”. Related definitions of other terms will be given in the following description. It should be noted that the “first”, “second”, etc. concepts mentioned in the present disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0026] It should be noted that the modification of "one", "a plurality of" mentioned in the present disclosure is illustrative but not restrictive, and those skilled in the art should understand that unless the context clearly indicates otherwise, it should be understood as "one or more".

[0027] Referring to Figures 1 to 7 As shown in the figure, the present embodiment provides a pre-cooling heat exchanger for aircraft. The aircraft includes a propulsion channel 200, an engine 300 and a pre-cooling heat exchanger 100. Wherein the pre-cooling heat exchanger 100 and the engine 300 are located in the propulsion channel 200, one end of the propulsion channel 200 forms an air inlet, the other end of the propulsion channel 200 has a tail nozzle 400, the pre-cooling heat exchanger 100 is located on the air inlet side of the engine 300, and the pre-cooling heat exchanger 100 is used to cool the air entering the propulsion channel 200 from the air inlet, thereby cooling the air inlet temperature of the engine 300, ensuring the performance of the engine 300, and further ensuring that it can fly at a higher speed. The air is finally ejected from the tail nozzle 400 to provide thrust for the aircraft.

[0028] The pre-cooling heat exchanger 100 for aircraft includes a shell and a heat exchange core 10 located in the shell. Referring to Figure 2 As shown in the figure, the heat exchange core 10 includes at least three layers of spaced apart baffles 1.

[0029] Among every three adjacent baffles 1, two adjacent baffles 1 form an air flow channel 11 therebetween, and the other two adjacent baffles 1 form a heat exchange working medium flow channel 12 therebetween. The air flow channel 11 is arranged along a first direction of the baffle 1, and the air flow channel 11 is provided with heat exchange fins 111. The heat exchange working medium flow channel 12 is arranged along a second direction of the baffle 1. The first direction and the second direction are perpendicular. That is, the cross-flow plate fin heat exchanger is formed by such arrangement.

[0030] Wherein, the first direction may be, for example, the length direction of the baffle 1, such as Figure 2 X direction in the figure, and the second direction may be, for example, the width direction of the baffle 1, such as Figure 2 Y direction in the figure.

[0031] The heat exchange working medium exchanges heat with the air in the adjacent air flow channel 11 in the flow process, absorbs the heat of the air, realizes the cooling of the air, and the heat exchange working medium after heat exchange is finally discharged from the outlet of the heat exchange working medium flow channel 12.

[0032] Specifically, the heat of the air entering into the air flow channel 11 is transferred to the partition plate 1, and is transferred to the heat exchange working medium in the adjacent heat exchange working medium flow channel 12 by the partition plate 1 and the heat exchange fin 111. The heat exchange working medium absorbs the air heat and then flows out from the outlet of the heat exchange working medium flow channel 12, so as to realize the cooling of the air. The cooled air in the air flow channel 11 finally flows to the engine 300 from the outlet end of the air flow channel 11, enters the engine 300 from the air inlet of the engine 300, so as to realize the cooling of the air inlet temperature of the engine 300, ensure the performance of the engine 300, and further ensure that the engine 300 can fly at a higher speed.

[0033] In combination Figures 2 to 4 As shown in the figure, in the first direction, the heat exchange core 10 sequentially includes a high-temperature section area 13, a medium-temperature section area 14 and a low-temperature section area 15. It can be understood that the air entering from the air inlet of the propulsion channel 200 passes through the high-temperature section area 13, the medium-temperature section area 14 and the low-temperature section area 15 in sequence, and the temperature of the air gradually decreases.

[0034] The pre-cooling heat exchanger 100 provided by the embodiment of the present disclosure is used in an aero-engine air source system, and can cool the high-temperature gas of 1200K to 600K, realize the cooling of the air inlet temperature, ensure the normal work of the engine 300, and make the engine 300 fly at a high speed.

[0035] For example, the air temperature corresponding to the high-temperature section area 13 is 1200K-900K, the air temperature corresponding to the medium-temperature section area 14 is 900K-700K, and the air temperature corresponding to the low-temperature section area 15 is 700K-600K.

[0036] The partition plate 1 and the heat exchange fin 111 located in the high-temperature section area 13 are made of nickel-based alloy material, the partition plate 1 and the heat exchange fin 111 located in the medium-temperature section area 14 are made of titanium-aluminum alloy material, and the partition plate 1 and the heat exchange fin 111 located in the low-temperature section area 15 are made of aluminum alloy material.

[0037] The nickel-based high-temperature alloy is used as the material of the partition plate 1 and the fin in the high-temperature section area 13. The nickel-based alloy has excellent high-temperature strength, oxidation resistance and corrosion resistance, and can maintain structural stability at extremely high temperatures. The titanium-aluminum alloy is used as the material of the partition plate 1 and the fin in the medium-temperature section area 14. The titanium-aluminum alloy has high specific strength, high specific stiffness and excellent heat resistance, and performs outstandingly below 900K. In addition, the titanium-aluminum alloy is 40% lighter than the nickel-based alloy. The aluminum alloy is used as the material of the partition plate 1 and the fin in the low-temperature section area 15. The aluminum alloy has the characteristics of light weight, high strength, good heat conductivity and excellent processing performance, and has stable performance below 700K. In addition, the aluminum alloy is 65% lighter than the nickel-based alloy.

[0038] That is, the heat exchange core 10 of the precooling heat exchanger 100 is divided into three sections according to temperature intervals, and different materials are used in each section, so that at high temperatures, the partition plates 1 and fins of each section are well matched with the temperature of the corresponding section, avoiding the use of the same single material in different temperature sections, which leads to a mismatch in the thermal expansion coefficient, and further causes the partition plates 1 and other components of the heat exchange core 10 to deform, crack, and other problems. Moreover, since titanium-aluminum alloy and aluminum alloy are lighter than nickel-based alloy, compared to setting the materials of the medium-temperature section 14 and the low-temperature section 15 as nickel-based alloy, the disclosed embodiment as described above reduces the weight of the heat exchange core 10 by 40% to 60%, thereby meeting the strict weight constraints of airborne heat exchangers and improving the lightweight of the partition plates 1 and fins.

[0039] For example, the partition plates 1 and fins of the high-temperature section 13 can specifically use Inconel 625 or HAYNES747 nickel-based alloy. The partition plates 1 and fins of the medium-temperature section 14 can specifically use Ti-6242 or IMI-834 titanium-aluminum alloy. The partition plates 1 and fins of the low-temperature section 15 can specifically use Al 6061 or Al 7075 aluminum alloy. Such a setting further improves the temperature resistance of the partition plates 1 and fins of each section, further reduces the stress concentration coefficient, and improves the structural stability and service life of the entire heat exchange core 10.

[0040] The partition plate 1 of the high-temperature section 13 and the partition plate 1 of the medium-temperature section 14 are connected by a flexible expansion compensation member 2, and the partition plate 1 of the medium-temperature section 14 and the partition plate 1 of the low-temperature section 15 are also connected by a flexible expansion compensation member 2.

[0041] By connecting the two adjacent sections by the flexible expansion compensation member 2, the stress concentration at the interface of different materials can be effectively alleviated due to the flexibility of the flexible expansion compensation member 2, further reducing the stress concentration coefficient and avoiding deformation and cracking, thereby avoiding deformation and damage of the heat exchanger.

[0042] Referring to Figure 2 , Figure 4 and Figure 6 , in the second direction, part of the plate section of the partition plate 1 is formed into a zigzag plate section 16, which utilizes the elastic deformation of the material of the partition plate 1 to absorb thermal expansion at high temperatures, effectively solving the macroscopic expansion problem from cold state to hot state, reducing the stress concentration coefficient, without the need for additional weight, significantly improving the thermal fatigue life of the heat exchanger, avoiding damage to the heat exchanger, and ensuring stable operation of the precooling heat exchanger 100 under high-temperature working conditions.

[0043] Tests show that the zigzag partition plate 1 design can accommodate at least 5mm of expansion per meter length, and the flexible expansion compensation member 2 can achieve displacement compensation (±2mm) in the first direction, thereby effectively solving the macroscopic expansion problem from cold state to hot state and ensuring stable operation of the heat exchanger under high temperature working conditions.

[0044] In some embodiments, the heat exchange working medium can be a liquid metal, which has high thermal conductivity (thermal conductivity coefficient 24-70W / m·K) and a wide liquid temperature range (up to 2000℃), can effectively cool the high-temperature incoming flow, and further improve the heat exchange efficiency and the cooling effect on air.

[0045] For example, the liquid metal can be a high-boiling gallium-indium-tin Ga-In-Sn alloy (mass fraction: Ga 70%, In 20%, Sn 10%), with a thermal conductivity coefficient of about 35W / m·K and a circulation flow rate of 10L / min, thereby effectively cooling the high-temperature incoming flow.

[0046] Of course, in other implementations, the heat exchange working medium can also be sodium-potassium alloy, lead-bismuth alloy, etc., and the embodiments of the present disclosure are not limited thereto.

[0047] The pre-cooling heat exchanger 100 for aircraft provided by the embodiments of the present disclosure includes at least three partition plates 1 arranged in layers and at intervals, so that two adjacent partition plates 1 among every three adjacent partition plates 1 form an air flow channel 11, and the other two adjacent partition plates 1 form a heat exchange working medium flow channel 12 for the flow of the heat exchange working medium, a heat exchange fin 111 is arranged in the air flow channel 11, and the air flow channel 11 and the heat exchange working medium flow channel 12 are arranged vertically, thereby improving the heat exchange efficiency.

[0048] By sequentially including the high-temperature section area 13, the medium-temperature section area 14 and the low-temperature section area 15 along the first direction, the baffle 1 and the heat exchange fin 111 located in the high-temperature section area 13 are both made of nickel-based alloy material, which improves the high-temperature strength, oxidation resistance and corrosion resistance of the baffle 1 and the heat exchange fin 111 in the high-temperature section area 13, so that the baffle 1 and the heat exchange fin 111 in the high-temperature section area 13 can maintain structural stability at extremely high temperature; the baffle 1 and the heat exchange fin 111 located in the medium-temperature section area 14 are both made of titanium-aluminum alloy material, which improves the high specific strength, high specific stiffness and heat resistance of the baffle 1 and the heat exchange fin 111 in the medium-temperature section area 14, and greatly reduces the weight of the heat exchange core 10; the baffle 1 and the heat exchange fin 111 located in the low-temperature section area 15 are both made of aluminum alloy material, which improves the heat conduction performance and stability of the baffle 1 and the heat exchange fin 111 in the low-temperature section area 15, and greatly reduces the weight of the heat exchange core 10. That is, by matching the corresponding materials in different temperature section areas of the heat exchange core 10, the material of the baffle 1 and the fin in each section area is better matched with the temperature of the corresponding section area at high temperature, avoiding the mismatch of the thermal expansion coefficient caused by using the same single material in different temperature section areas, and further avoiding the deformation, cracking and other situations of the baffle of the heat exchange core, and such arrangement also realizes the lightweight of the heat exchange core 10, so that the pre-cooling heat exchanger 100 meets the strict requirements of airborne equipment on weight.

[0049] Meanwhile, the baffle 1 in the high-temperature section area 13 and the baffle 1 in the medium-temperature section area 14, and the baffle 1 in the medium-temperature section area 14 and the baffle 1 in the low-temperature section area 15 are all connected through the flexible expansion compensation member 2, which effectively relieves the stress concentration at the interface of different materials, reduces the stress concentration coefficient, avoids deformation and cracking, and thus avoids deformation and damage of the heat exchanger.

[0050] Moreover, along the second direction, part of the baffle 1 is formed into a zigzag plate section 16, so that the baffle 1 can utilize the elastic deformation of its own material to effectively absorb the thermal expansion of the metal baffle at high temperature, effectively solve the macroscopic expansion problem of the metal material from cold state to hot state, further reduce the stress concentration coefficient, improve the thermal fatigue life of the heat exchanger, avoid damage of the heat exchanger, and ensure the stable operation of the pre-cooling heat exchanger 100 under high temperature working condition.

[0051] In some embodiments, along the first direction, the length ratio of the high-temperature section area 13, the medium-temperature section area 14 and the low-temperature section area 15 can be 2:3:3. In this way, the size of each section area can be better matched with the corresponding air temperature, and thus the thermal stress of the baffle 1 and the heat exchange fin 111 in the corresponding section area is further reduced, and the deformation, cracking and other situations of the baffle 1 and the heat exchange fin 111 are avoided.

[0052] Exemplarily, the overall size of the pre-cooling heat exchanger 100 is, for example, 800 mm x 600 mm x 200 mm, and the total weight is controlled to be, for example, less than 15 kg. At this time, the length of the high-temperature section 13 can be set to 200 mm, the length of the medium-temperature section 14 can be set to 300 mm, and the length of the low-temperature section 15 can be set to 300 mm.

[0053] Exemplarily, the thickness of the baffle 1 of the high-temperature section 13 can be set to 0.4 mm, and the thickness of the fin of the high-temperature section 13 can be set to 0.1 mm. The thickness of the baffle 1 of the medium-temperature section can be set to 0.3 mm, and the thickness of the fin of the medium-temperature section can be set to 0.08 mm. The thickness of the baffle 1 of the low-temperature section 15 can be set to 0.3 mm, and the thickness of the fin of the low-temperature section 15 can be set to 0.06 mm.

[0054] The thickness of the fin can be specifically the thickness dimension of the fin in the second direction.

[0055] Referring to Figs. 1 and 2, in some embodiments, the flexible expansion compensation member 2 is a curved structure extending in the first direction, and the curved structure includes at least one U-shaped section 21. Figure 2 Figure 4 Since the flexible expansion compensation member 2 is a curved structure and includes at least one U-shaped section 21, the flexible expansion compensation member 2 can effectively buffer the stress at the interface of different materials and the thermal expansion of the materials at high temperatures, further improving the structural reliability of the heat exchange core 10. Figure 5 In some embodiments, the flexible expansion compensation member 2 is a curved alloy foil sheet formed by pressing an alloy foil. In this way, the manufacturing is simple, and the buffering effect of the flexible expansion compensation member 2 on thermal stress and high-temperature thermal expansion is further improved.

[0056] Exemplarily, the thickness of the alloy foil is, for example, 0.3 mm.

[0057] Referring to Figs. 1 and 2, the flexible expansion compensation member 2 can specifically include one U-shaped member. In other implementations, the flexible expansion compensation member 2 can also include a plurality of U-shaped members connected in sequence, that is, the flexible expansion compensation member 2 can be formed in a generally wavy structure.

[0058] Continuing to refer to Fig. 1, in some embodiments, in the height direction of the heat exchange core 10, the height of the flexible expansion compensation member 2 is not greater than half the height of the air flow channel 11. The height of the flexible expansion compensation member 2 here is specifically the height dimension of the flexible expansion compensation member 2 in the height direction of the heat exchange core 10.

[0059] Figure 4 In some embodiments, the flexible expansion compensation member 2 is a curved alloy foil sheet formed by pressing an alloy foil. In this way, the manufacturing is simple, and the buffering effect of the flexible expansion compensation member 2 on thermal stress and high-temperature thermal expansion is further improved. Figure 5 Continuing to refer to Fig. 1, in some embodiments, in the height direction of the heat exchange core 10, the height of the flexible expansion compensation member 2 is not greater than half the height of the air flow channel 11. The height of the flexible expansion compensation member 2 here is specifically the height dimension of the flexible expansion compensation member 2 in the height direction of the heat exchange core 10.

[0060] Figure 5 Continuing to refer to Fig. 1, in some embodiments, in the height direction of the heat exchange core 10, the height of the flexible expansion compensation member 2 is not greater than half the height of the air flow channel 11. The height of the flexible expansion compensation member 2 here is specifically the height dimension of the flexible expansion compensation member 2 in the height direction of the heat exchange core 10.​​​Figure 5 The size h in the formula, i.e. the height of the part of the flexible expansion compensation member 2 located in the air flow channel 11.

[0061] Thus, in the case of reducing thermal stress and high-temperature thermal expansion, the flexible expansion compensation member 2 does not affect the normal flow of air in the air flow channel 11, thereby ensuring the air intake amount and air intake efficiency, and further ensuring the thrust of the aircraft.

[0062] In some embodiments, the width dimension of the U-shaped section 21 in the first direction can range from 20 mm to 30 mm. Here, the width dimension is specifically the size a in the formula. Figure 5

[0063] As set forth above, the flexible expansion compensation member 2 can maintain good flexibility and pressure-bearing capacity at high temperatures, ensuring the pressure-bearing capacity of the entire partition plate 1 while ensuring good buffering of the flexible expansion compensation member 2 to thermal stress and thermal expansion, further avoiding deformation and damage of the partition plate 1, etc. Moreover, the flexible expansion compensation member 2 does not affect the normal flow of air in the air flow channel 11, thereby ensuring the air intake amount and air intake efficiency, and further ensuring the thrust of the aircraft.

[0064] In the formula, the material of the flexible expansion compensation member 2 between the high-temperature section area 13 and the medium-temperature section area 14 can be the same nickel-based alloy material as the material of the partition plate 1 of the high-temperature section area 13, or can be the same titanium-aluminum alloy material as the material of the partition plate 1 of the medium-temperature section area 14. The flexible expansion compensation member 2 is connected between the high-temperature section area 13 and the medium-temperature section area 14, for example, by vacuum brazing.

[0065] In the formula, the material of the flexible expansion compensation member 2 between the medium-temperature section area 14 and the low-temperature section area 15 can be the same titanium-aluminum alloy material as the material of the partition plate 1 of the medium-temperature section area 14, or can be the same aluminum alloy material as the material of the partition plate 1 of the low-temperature section area 15. The flexible expansion compensation member 2 is connected between the medium-temperature section area 14 and the low-temperature section area 15, for example, by vacuum brazing.

[0066] In some embodiments, the sawtooth angle of the sawtooth plate section 16 can range from 60° to 90°, for example, the sawtooth angle is 75°.

[0067] Through finite element optimization, such a setting can reduce the stress concentration coefficient to below 1.2, significantly improving the thermal fatigue life of the heat exchanger.

[0068] As shown in Figure 2 and Figure 4 When implemented, the two sides of the air flow channel 11 in the first direction and the two sides of the heat exchange working medium flow channel 12 in the second direction are both provided with the sealing strip 3. Figure 2 and Figure 4 ​The sealing strip on one side of the hollow air flow channel 11 is not shown. It can be understood that the two partition plates 1 corresponding to the air flow channel 11 and the sealing strips 3 on the two sides thereof jointly enclose the air flow channel 11, and the two partition plates 1 corresponding to the heat exchange working medium flow channel 12 and the sealing strips 3 on the two sides thereof jointly enclose the heat exchange working medium flow channel 12.

[0069] Referring to Figure 7 As shown in the figure, the sealing strip 3 comprises a body layer 31 and an elastic layer 32 located outside the body layer 31. In this way, the sealing strip 3 is formed as a flexible sealing strip, and the elastic layer 32 can expand at high temperature, realizing the expansion self-compensation of the sealing strip 3 at high temperature, and the sealing strip 3 remains sealed at low temperature, ensuring the sealing reliability of the heat exchanger under high temperature working conditions.

[0070] In some embodiments, the body layer 31 can be specifically a nickel-based alloy foil layer, and the elastic layer 32 can be specifically a silicone rubber layer.

[0071] For example, the sealing strip 3 adopts a 0.1mm-thick Inconel 625 alloy foil and a high-temperature vulcanized silicone rubber composite structure, and the cross-sectional size of the sealing strip 3 is 3mm x 5mm. The alloy foil adopts a nickel-based high-temperature alloy (such as Inconel 625), which has excellent high-temperature resistance and corrosion resistance. The silicone rubber, such as high-temperature vulcanized silicone rubber (HTV), has excellent high-temperature performance (up to 260℃), and at the same time has good adhesion with the high-temperature alloy foil.

[0072] The sealing strip 3 is designed to adopt a super-thin high-temperature alloy foil and a silicone rubber composite structure, and the rubber softening allows transverse expansion at high temperature, and remains sealed at low temperature, realizing a thermal expansion self-compensation structure, effectively solving the sealing problem of liquid metal cooling, and ensuring the sealing reliability of the heat exchanger under high temperature working conditions.

[0073] Of course, in other implementations, the body layer 31 can also be selected from other metal materials, and the elastic layer 32 can also be selected from other materials that can expand at high temperature.

[0074] The embodiment of the present disclosure proposes a partitioned cross-flow plate fin pre-cooling heat exchanger, which realizes lightweight, low stress and high reliability at high temperature through material partitioning, flexible connection, structure self-compensation and composite sealing strip design, and solves the problems of thermal stress, macroscopic expansion and weight constraint faced by high-temperature pre-cooling.

[0075] Referring to Figure 1 As shown in the figure, the present disclosure also provides an aircraft, which comprises a propulsion channel 200, a pre-cooling heat exchanger 100 and an engine 300.

[0076] The pre-cooling heat exchanger 100 and the engine 300 are both located in the propulsion channel 200, one end of the propulsion channel 200 forms an air inlet, the other end of the propulsion channel 200 has a tail nozzle 400, and the pre-cooling heat exchanger 100 is located on the air inlet side of the engine 300.

[0077] The pre-cooling heat exchanger 100 is used to cool the air entering from the air inlet, and the cooled air enters the engine 300 and is finally sprayed out from the tail nozzle 400 to provide flight thrust for the aircraft.

[0078] The pre-cooling heat exchanger 100 in the embodiment of the present disclosure has the same specific structure and implementation principle as the pre-cooling heat exchanger 100 for the aircraft provided in the above embodiment, and can bring the same or similar technical effects, and will not be described one by one here, and the specific description can be referred to the description of the above embodiment.

[0079] The above description is only some embodiments of the present disclosure and an explanation of the technical principles applied. Those skilled in the art should understand that the disclosure range 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 equivalent features without departing from the above disclosed concept. For example, the technical solutions formed by replacing the above features with the technical features disclosed in the present disclosure (but not limited to) having similar functions.

[0080] Although some specific embodiments of the present disclosure have been described in detail through examples, those skilled in the art should understand that the above examples are only for illustration, not for limiting 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 precooling heat exchanger for aircraft, characterized in that, The device includes a heat exchange core comprising at least three stacked and spaced-apart partitions. In every three adjacent partitions, an airflow channel is formed between two adjacent partitions, and a heat exchange medium flow channel is formed between the other two adjacent partitions. The airflow channel is arranged along a first direction of the partitions and contains heat exchange fins. The heat exchange medium flow channel is arranged along a second direction of the partitions; the first direction and the second direction are perpendicular to each other. Along the first direction, the heat exchange core sequentially includes a high-temperature section, a medium-temperature section, and a low-temperature section. The partitions and heat exchange fins in the high-temperature section are made of nickel-based alloy, the partitions and heat exchange fins in the medium-temperature section are made of titanium-aluminum alloy, and the partitions and heat exchange fins in the low-temperature section are made of aluminum alloy. The partitions in the high-temperature zone and the medium-temperature zone, as well as the partitions in the medium-temperature zone and the low-temperature zone, are all connected by flexible expansion compensation components. Along the second direction, some segments of the partition are formed as serrated segments.

2. The precooling heat exchanger for aircraft according to claim 1, characterized in that, The flexible expansion compensation component is a curved structure that bends and extends along the first direction. The curved structure includes at least one U-shaped segment, which is recessed toward the inner cavity of the airflow channel.

3. The precooling heat exchanger for aircraft according to claim 2, characterized in that, Along the height direction of the heat exchange core, the height of the flexible expansion compensation member is no greater than half the height of the airflow channel; And / or, the width of the U-shaped segment along the first direction is in the range of 20mm to 30mm.

4. The precooling heat exchanger for aircraft according to claim 2, characterized in that, The flexible expansion compensation component is a curved alloy foil sheet formed by pressing an alloy foil.

5. The precooling heat exchanger for aircraft according to any one of claims 1 to 4, characterized in that, Seals are provided on both sides of the air flow channel along the first direction and on both sides of the heat exchange medium flow channel along the second direction. The seal includes a body layer and an elastic layer located outside the body layer.

6. The precooling heat exchanger for aircraft according to claim 5, characterized in that, The body layer is a nickel-based alloy foil layer, and the elastic layer is a silicone rubber layer.

7. The precooling heat exchanger for aircraft according to any one of claims 1 to 4, characterized in that, The serrated plate segment has a serration angle range of 60° to 90°.

8. The precooling heat exchanger for aircraft according to any one of claims 1 to 4, characterized in that, Along the first direction, the length ratio of the high-temperature section, the medium-temperature section, and the low-temperature section is 2:3:

3.

9. The precooling heat exchanger for aircraft according to any one of claims 1 to 4, characterized in that, The heat exchange medium is liquid metal.

10. An aircraft, characterized in that, Includes an engine and an aircraft precooling heat exchanger as described in any one of claims 1 to 9; The precooling heat exchanger for the aircraft is located on the intake side of the engine.

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