A spiral multi-fluid aviation pre-cooling heat exchanger

Abstract

The present invention discloses a spiral multi-fluid aviation pre-cooling heat exchanger, which belongs to the field of heat exchangers. The heat exchanger includes a main cooling fuel cooling section and an auxiliary cooling fuel physical cooling section. The main cooling fuel cooling section not only cools the high-temperature air through the high-temperature catalytic cracking heat absorption of the main cooling fuel, but also cools the high-temperature air through the physical heat absorption (including sensible heat and latent heat) of the main cooling fuel; the auxiliary cooling fuel physical cooling section cools the high-temperature air through the physical heat absorption of the auxiliary cooling fuel, and the high-temperature air passes through the main cooling fuel cooling section and the auxiliary cooling fuel physical cooling section in sequence, thereby achieving a cooling effect. On the basis of meeting the heat exchange capacity requirements, pressure recovery coefficient and pressure drop, the present invention optimizes the heat exchanger structural parameters to maximize the power-to-weight ratio and reduce the weight of the heat exchanger.

Description

Technical Field

[0001] The invention belongs to the field of heat exchangers, and in particular relates to a spiral multi-fluid aviation pre-cooling heat exchanger. Background Art

[0002] Lightweight, high-power precoolers are key components in aircraft engine thermodynamic cycles. Their mission is to extract sufficient heat from incoming air in a very short time to reduce the air temperature. The design of a precooler for a composite precooling cycle engine requires the highest possible heat transfer efficiency and the lowest possible mass while meeting the cycle's requirements. To this end, the smaller the heat transfer tube diameter, the better, while still meeting the system's flow resistance requirements. Therefore, international precoolers typically utilize compact shell-and-tube microchannel heat exchangers.

[0003] Currently, the primary cooling solution for pre-cooled combined cycle engines is heat exchanger pre-cooling. This cooling method involves placing a heat exchanger in the intake duct, allowing air to pass through the heat exchanger walls and exchange heat with the low-temperature coolant inside the heat exchanger through convection. Examples include the Japanese Pre-cooled Turbojet (PCTJ), the Japanese Expander Cycle AirTurbo Ramjet Engine (ATRE), and the British Synergistic Air-Breathing Rocket Engine (SABER). Since the 1980s, extensive research on pre-cooled combined cycle engines has been conducted internationally.

[0004] There are still some difficulties in the design of precooler:

[0005] (1) The problem of increased flow resistance when the intake air flows through the fuel channel, resulting in increased total pressure loss, is a chronic problem of pre-cooling engines;

[0006] (2) The design of the precooler should comprehensively consider the structure, hydraulics, and mechanical design of the heat exchanger, including the layout of the heat exchanger, the selection of heat exchange channel size parameters, the selection of flow type, the determination of heat exchanger materials, and other issues;

[0007] (3) Generally speaking, the most direct way to enhance the heat transfer capacity of a heat exchanger is to increase the heat transfer surface area. When the installation space cannot be changed, the only way to enhance the heat transfer capacity is to reduce the hydraulic diameter of the heat transfer channel. However, the pressure drop of the heat exchanger channel is inversely proportional to the hydraulic diameter. Unlimited reduction of the channel size is harmful to the performance of the heat exchanger. Finding a balance between pressure drop and surface area density is the key point in precooler design.

[0008] Therefore, it is necessary to design a new precooler structure to solve the above problems. Summary of the Invention

[0009] In view of the technical defects and technical drawbacks in the existing technology, the present invention proposes a new precooler design structure. The heat exchanger meets the heat exchange capacity requirements, pressure recovery coefficient and pressure drop, and optimizes the heat exchanger structural parameters to maximize the power-to-weight ratio and reduce the weight of the heat exchanger.

[0010] To achieve the above objectives, the present invention adopts the following technical solutions: a spiral multi-fluid aviation pre-cooling heat exchanger, comprising a main cooling fuel cooling section and an auxiliary cooling fuel physical cooling section, wherein the main cooling fuel cooling section is located on the periphery of the auxiliary cooling fuel physical cooling section, and the main cooling fuel cooling section not only cools the high-temperature air by absorbing heat through high-temperature catalytic cracking of the main cooling fuel, but also cools the high-temperature air through physical absorption of heat by the main cooling fuel; the auxiliary cooling fuel physical cooling section cools the high-temperature air through physical absorption of heat by the auxiliary cooling fuel; the high-temperature air cooled by the heat exchanger passes through the main cooling fuel cooling section and the auxiliary cooling fuel physical cooling section in sequence, thereby achieving a cooling effect;

[0011] The main cooling fuel cooling section includes a primary manifold outlet pipe of the main cooling fuel cooling section, a primary manifold inlet pipe of the main cooling fuel cooling section, a plurality of secondary manifold outlet pipes of the main cooling fuel cooling section, a plurality of secondary manifold inlet pipes of the main cooling fuel cooling section and a plurality of main cooling fuel cooling section spiral pipes. The primary manifold outlet pipe of the main cooling fuel cooling section is located at the periphery of the primary manifold inlet pipe of the main cooling fuel cooling section. A plurality of secondary manifold outlet pipes of the main cooling fuel cooling section are vertically arranged on the primary manifold outlet pipe of the main cooling fuel cooling section. A plurality of secondary manifold inlet pipes of the main cooling fuel cooling section are vertically arranged on the primary manifold inlet pipe of the main cooling fuel cooling section. The main cooling fuel cooling section spiral pipe connects the secondary manifold outlet pipe of the main cooling fuel cooling section and the secondary manifold inlet pipe of the main cooling fuel cooling section.

[0012] The auxiliary cooling fuel physical cooling section includes an auxiliary cooling fuel physical cooling section first-level manifold water outlet pipe 6, an auxiliary cooling fuel physical cooling section first-level manifold water inlet pipe, several auxiliary cooling fuel physical cooling section second-level manifold water outlet pipes, several auxiliary cooling fuel physical cooling section second-level manifold water inlet pipes, and several auxiliary cooling fuel physical cooling section spiral pipes. The auxiliary cooling fuel physical cooling section first-level manifold water outlet pipe is located on the periphery of the auxiliary cooling fuel physical cooling section first-level manifold water inlet pipe. Several auxiliary cooling fuel physical cooling section second-level manifold water outlet pipes are vertically arranged on the auxiliary cooling fuel physical cooling section first-level manifold water outlet pipe. Several auxiliary cooling fuel physical cooling section second-level manifold water inlets are vertically arranged on the auxiliary cooling fuel physical cooling section first-level manifold water inlet pipe. The auxiliary cooling fuel physical cooling section spiral pipe connects the auxiliary cooling fuel physical cooling section second-level manifold water outlet pipe and the auxiliary cooling fuel physical cooling section second-level manifold water inlet pipe.

[0013] Furthermore, the main cooling fuel cooling section spiral tube and the auxiliary cooling fuel physical cooling section spiral tube adopt Archimedean spiral.

[0014] Furthermore, the main cooling fuel cooling section spiral tubes and the auxiliary cooling fuel physical cooling section spiral tubes are arranged clockwise or counterclockwise.

[0015] Furthermore, the main cooling fuel cooling section spiral pipe is evenly arranged axially between the main cooling fuel cooling section secondary manifold outlet pipe and the main cooling fuel cooling section secondary manifold inlet pipe.

[0016] Furthermore, the spiral tubes of the auxiliary cooling fuel physical cooling section are evenly arranged axially between the auxiliary cooling fuel physical cooling section secondary manifold water outlet pipe and the auxiliary cooling fuel physical cooling section secondary manifold water inlet pipe.

[0017] Furthermore, the primary manifold outlet pipe of the main cooling fuel cooling section, the primary manifold inlet pipe of the main cooling fuel cooling section, the primary manifold outlet pipe of the auxiliary cooling fuel physical cooling section and the primary manifold inlet pipe of the auxiliary cooling fuel physical cooling section are ring-shaped.

[0018] Furthermore, the main cooling fuel flows into the primary manifold inlet of the main cooling fuel cooling section, and flows in sequence through the secondary manifold inlet of the main cooling fuel cooling section, the spiral tube of the main cooling fuel cooling section, the secondary manifold outlet of the main cooling fuel cooling section and the primary manifold outlet of the main cooling fuel cooling section, and cools the high-temperature air through the main cooling fuel cooling section.

[0019] Furthermore, the auxiliary cooling fuel flows into the auxiliary cooling fuel physical cooling section from the first-level manifold water inlet pipe, and flows in sequence through the auxiliary cooling fuel physical cooling section second-level manifold water inlet pipe, the auxiliary cooling fuel physical cooling section spiral pipe, the auxiliary cooling fuel physical cooling section second-level manifold water outlet pipe, and the auxiliary cooling fuel physical cooling section first-level manifold water outlet pipe, and cools the high-temperature air through the auxiliary cooling fuel physical cooling section.

[0020] Furthermore, the inner walls of the pipelines of the main cooling fuel cooling section are coated with a high-efficiency catalyst.

[0021] Furthermore, the secondary manifold outlet pipes of the main cooling fuel cooling section are evenly arranged circumferentially on the primary manifold outlet pipe of the main cooling fuel cooling section; the secondary manifold inlet pipes of the main cooling fuel cooling section are evenly arranged circumferentially on the primary manifold inlet pipe of the main cooling fuel cooling section; the secondary manifold inlet pipes of the auxiliary cooling fuel physical cooling section are evenly arranged circumferentially on the primary manifold inlet pipe of the auxiliary cooling fuel physical cooling section; the secondary manifold outlet pipes of the auxiliary cooling fuel physical cooling section are evenly arranged circumferentially on the primary manifold outlet pipe of the auxiliary cooling fuel physical cooling section.

[0022] Compared with the prior art, the spiral multi-fluid aviation pre-cooling heat exchanger of the present invention has the following beneficial effects:

[0023] 1. The spiral multi-fluid aviation pre-cooling heat exchanger described in the present invention is cooled through two heat exchange sections: the main cooling fuel cooling section and the auxiliary cooling fuel physical cooling section. First, high-temperature air flows through the main cooling fuel cooling section. The main cooling fuel undergoes a catalytic cracking reaction under the action of a high-efficiency catalyst to produce hydrogen, carbon monoxide, and small-molecule organic matter. This reaction can absorb a large amount of heat from the surface of the heat exchanger, playing a cooling role, improving the cooling effect of the heat exchanger, extending the service life of the heat exchanger, and enhancing the stability of the heat exchanger. Compared with traditional physical heat absorption methods, the introduction of chemical heat absorption and physical heat absorption to cool the high-temperature air simultaneously greatly improves the heat absorption capacity of the fuel. Preliminary experimental studies have shown that the total heat sink of the main cooling fuel can reach 2.3 times the total heat sink of traditional aviation kerosene fuel, significantly improving the heat exchange capacity of the pre-cooler. At the same time, the high-temperature air is cooled by the physical heat absorption of the main cooling fuel, including sensible heat and latent heat. Finally, the high-temperature air flows through the auxiliary cooling fuel physical cooling section, where the auxiliary cooling fuel physically absorbs sensible heat to cool the high-temperature air. The above high-temperature air is cooled in sections, making full use of the heat absorption capacity of the fuel at each stage and greatly improving the cooling effect of the heat exchanger.

[0024] 2. In the spiral multi-fluid aviation pre-cooling heat exchanger described in the present invention, hydrogen, carbon monoxide and small molecular organic matter generated during the cracking reaction can be transported to the combustion chamber for combustion, and the absorbed heat can be released again. By recycling the fuel, the fuel utilization efficiency is improved and energy waste is avoided.

[0025] 3. Compared with the traditional thermal cracking reaction, the catalytic cracking reaction adopted in the present invention can absorb more heat, and also improves the chemical heat absorption capacity of the main cooling fuel. In addition, the catalytic cracking reaction can effectively reduce the generation of carbon deposits and inhibit coking.

[0026] 4. The spiral multi-fluid aviation pre-cooling heat exchanger described in this invention utilizes Archimedean spirals for the primary fuel cooling section and the auxiliary fuel physical cooling section. Among various curves, the Archimedean spiral provides a larger heat exchange area within the same space, significantly improving the heat exchange capacity of the multi-stage annular pre-cooling heat exchanger. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings, which constitute part of the present invention, are provided to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are provided to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0028] Figure 1 This is a top view of a spiral multi-fluid aviation pre-cooling heat exchanger according to the present invention;

[0029] Figure 2 This is an overall schematic diagram of a spiral multi-fluid aviation pre-cooling heat exchanger according to the present invention;

[0030] In the figure: 1- primary manifold outlet pipe of the main cooling fuel cooling section, 2- secondary manifold outlet pipe of the main cooling fuel cooling section, 3- spiral pipe of the main cooling fuel cooling section, 4- secondary manifold inlet pipe of the main cooling fuel cooling section, 5- primary manifold inlet pipe of the main cooling fuel cooling section, 6- primary manifold outlet pipe of the auxiliary cooling fuel physical cooling section, 7- secondary manifold outlet pipe of the auxiliary cooling fuel physical cooling section, 8- spiral pipe of the auxiliary cooling fuel physical cooling section, 9- secondary manifold inlet pipe of the auxiliary cooling fuel physical cooling section, 10- primary manifold inlet pipe of the auxiliary cooling fuel physical cooling section, DETAILED DESCRIPTION

[0031] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0032] Exemplary embodiments will be described in detail herein, examples of which are illustrated in the accompanying drawings. In the following description, when referring to the drawings, like numbers in different figures represent like or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments are not intended to represent all possible embodiments consistent with the present invention. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the present invention, as detailed in the appended claims.

[0033] 1. Specific implementation method 1, see Figure 1 This embodiment describes a spiral multi-fluid aviation pre-cooling heat exchanger, comprising two heat exchange sections: a main cooling fuel cooling section and an auxiliary cooling fuel physical cooling section. The main cooling fuel cooling section is located outside the auxiliary cooling fuel physical cooling section. The main cooling fuel cooling section not only cools the high-temperature air through the high-temperature catalytic cracking heat absorption of the main cooling fuel, but also cools the high-temperature air through the physical absorption of the main cooling fuel. The auxiliary cooling fuel physical cooling section cools the high-temperature air through the physical absorption of the auxiliary cooling fuel. The high-temperature air cooled by the heat exchanger passes through the main cooling fuel cooling section and the auxiliary cooling fuel physical cooling section in sequence, thereby achieving a cooling effect.

[0034] The main cooling fuel cooling section includes a main cooling fuel cooling section primary manifold outlet pipe 1, a main cooling fuel cooling section primary manifold inlet pipe 5, a plurality of main cooling fuel cooling section secondary manifold outlet pipes 2, a plurality of main cooling fuel cooling section secondary manifold inlet pipes 4 and a plurality of main cooling fuel cooling section spiral pipes 3. The main cooling fuel cooling section primary manifold outlet pipe 1 is located on the periphery of the main cooling fuel cooling section primary manifold inlet pipe 5. A plurality of main cooling fuel cooling section secondary manifold outlet pipes 2 are vertically arranged on the main cooling fuel cooling section primary manifold outlet pipe 1. A plurality of main cooling fuel cooling section secondary manifold inlet pipes 4 are vertically arranged on the main cooling fuel cooling section primary manifold inlet pipe 5. The main cooling fuel cooling section spiral pipe 3 connects the main cooling fuel cooling section secondary manifold outlet pipe 2 and the main cooling fuel cooling section secondary manifold inlet pipe 4;

[0035] The auxiliary cooling fuel physical cooling section includes an auxiliary cooling fuel physical cooling section first-level manifold water outlet pipe 6, an auxiliary cooling fuel physical cooling section first-level manifold water inlet pipe 10, several auxiliary cooling fuel physical cooling section second-level manifold water outlet pipes 7, several auxiliary cooling fuel physical cooling section second-level manifold water inlet pipes 9, and several auxiliary cooling fuel physical cooling section spiral tubes 8. The auxiliary cooling fuel physical cooling section first-level manifold water outlet pipe 6 is located on the periphery of the auxiliary cooling fuel physical cooling section first-level manifold water inlet pipe 10. Several auxiliary cooling fuel physical cooling section second-level manifold water outlet pipes 7 are vertically arranged on the auxiliary cooling fuel physical cooling section first-level manifold water outlet pipe 6. Several auxiliary cooling fuel physical cooling section second-level manifold water inlet pipes 9 are vertically arranged on the auxiliary cooling fuel physical cooling section first-level manifold water inlet pipe 10. The auxiliary cooling fuel physical cooling section spiral tubes 8 connect the auxiliary cooling fuel physical cooling section second-level manifold water outlet pipe 7 and the auxiliary cooling fuel physical cooling section second-level manifold water inlet pipe 9.

[0036] Before the high-temperature air is introduced, the main cooling fuel flows in from the primary manifold inlet pipe 4 of the primary cooling fuel cooling section, and flows sequentially through the secondary manifold inlet pipe 5 of the primary cooling fuel cooling section, the spiral pipe 3 of the primary cooling fuel cooling section, the secondary manifold outlet pipe 2 of the primary cooling fuel cooling section, and the primary manifold outlet pipe 1 of the primary cooling fuel cooling section, thereby cooling the high-temperature air. The auxiliary cooling fuel flows in from the primary manifold inlet pipe 10 of the auxiliary cooling fuel physical cooling section, and flows sequentially through the secondary manifold inlet pipe 9 of the auxiliary cooling fuel physical cooling section, the spiral pipe 8 of the auxiliary cooling fuel physical cooling section, the secondary manifold outlet pipe 7 of the auxiliary cooling fuel physical cooling section, and the primary manifold outlet pipe 6 of the auxiliary cooling fuel physical cooling section, thereby cooling the high-temperature air.

[0037] The heat exchanger is designed to meet heat exchange requirements, pressure recovery coefficient, and pressure drop, and optimize heat exchanger structural parameters to maximize power-to-weight ratio and reduce heat exchanger mass.

[0038] In an embodiment of the present invention, the primary manifold outlet pipe 1 of the main cooling fuel cooling section, the primary manifold inlet pipe 5 of the main cooling fuel cooling section, the primary manifold outlet pipe 6 of the auxiliary cooling fuel physical cooling section, and the primary manifold inlet pipe 10 of the auxiliary cooling fuel physical cooling section are annular.

[0039] In an embodiment of the present invention, the inner wall of the main cooling fuel cooling section is coated with a high-efficiency catalyst.

[0040] In the embodiment of the present invention, the primary fuel cooling section spiral tube 3 and the auxiliary fuel physical cooling section spiral tube 8 are Archimedean spirals, which can be in the same direction or in opposite directions. Among various curves, the Archimedean spiral can provide a larger heat exchange area in the same space.

[0041] The main cooling fuel cooling section spiral tube 3 and the auxiliary cooling fuel physical cooling section spiral tube 8 are arranged clockwise or counterclockwise.

[0042] The main cooling fuel cooling section spiral tubes 3 are evenly arranged axially between the main cooling fuel cooling section secondary manifold outlet pipe 2 and the main cooling fuel cooling section secondary manifold inlet pipe 4.

[0043] The auxiliary cooling fuel physical cooling section spiral tubes 8 are evenly arranged axially between the auxiliary cooling fuel physical cooling section secondary manifold water outlet pipe 7 and the auxiliary cooling fuel physical cooling section secondary manifold water inlet pipe 9.

[0044] The specific number of axially evenly arranged tubes depends on the required heat exchange capacity of the air and the heat exchange capacity that can be provided by the main cooling fuel and the auxiliary cooling fuel on a single spiral tube.

[0045] In the embodiments of the present invention, the catalytic cracking catalyst can be a non-precious metal catalyst having nickel or cobalt as the metal component and an alumina support, or a supported precious metal catalyst such as a platinum metal catalyst or a zirconium metal catalyst. In the embodiments of the present invention, the type of catalytic cracking catalyst is not limited, as long as it can achieve a catalytic reaction of the primary cooling fuel and does not affect the endothermic effect during the reaction process. Those skilled in the art can select a catalyst based on existing technologies in the field.

[0046] The spiral multi-fluid aviation precooling heat exchanger described in an embodiment of the present invention utilizes two heat exchange sections: a primary fuel cooling section and an auxiliary fuel physical cooling section. First, high-temperature air flows through the primary fuel cooling section. The primary fuel undergoes a catalytic cracking reaction under the action of a high-efficiency catalyst, producing hydrogen, carbon monoxide, and small organic molecules. This reaction absorbs a significant amount of heat from the heat exchanger surface, providing a cooling effect. This improves the heat exchanger's cooling efficiency, extends its service life, and enhances its stability. Compared to traditional physical heat absorption methods, the simultaneous use of chemical and physical heat absorption to cool the high-temperature air significantly enhances the fuel's heat absorption capacity. Preliminary experimental research has shown that the total heat sink of the primary fuel can reach 2.3 times that of traditional aviation kerosene fuel, significantly improving the precooler's heat exchange capacity. Simultaneously, the high-temperature air is cooled by the physical absorption of heat (both sensible and latent) by the primary fuel. Finally, the high-temperature air flows through the auxiliary fuel physical cooling section, where the physical absorption of heat by the auxiliary fuel also cools the high-temperature air. The above high-temperature air is cooled in sections, making full use of the heat absorption capacity of the fuel at each stage and greatly improving the cooling effect of the heat exchanger.

[0047] In the embodiment of the present invention, the secondary manifold outlet pipe 2 of the main cooling fuel cooling section is evenly arranged circumferentially on the primary manifold outlet pipe 1 of the main cooling fuel cooling section; the secondary manifold inlet pipe 4 of the main cooling fuel cooling section is evenly arranged circumferentially on the primary manifold inlet pipe 5 of the main cooling fuel cooling section; the secondary manifold outlet pipe 7 of the auxiliary cooling fuel physical cooling section is evenly arranged circumferentially on the primary manifold outlet pipe 6 of the auxiliary cooling fuel physical cooling section; and the secondary manifold inlet pipe 9 of the auxiliary cooling fuel physical cooling section is evenly arranged circumferentially on the primary manifold inlet pipe 10 of the auxiliary cooling fuel physical cooling section. The specific number of circumferentially evenly arranged pipes depends on the required heat exchange capacity of the air and the heat exchange capacity of the main cooling fuel and auxiliary cooling fuel on a single secondary manifold.

[0048] The spiral multi-fluid aviation pre-cooling heat exchanger described in an embodiment of the present invention utilizes the main cooling fuel as a coolant in the main cooling fuel cooling section. A catalytic cracking catalyst causes the main cooling fuel to undergo a catalytic cracking reaction, cooling the high-temperature air. Furthermore, the main cooling fuel undergoes a catalytic cracking reaction in its gaseous phase at a temperature of approximately 600K, generating small molecules that absorb significant heat during the cracking process, achieving excellent cooling performance. The products of the catalytic cracking reaction, such as hydrogen, carbon monoxide, and small organic gases, enter the combustion chamber and burn, releasing the absorbed heat.

[0049] The spiral multi-fluid aviation pre-cooling heat exchanger described in an embodiment of the present invention utilizes the combustion and cooling properties of the main cooling fuel and the auxiliary cooling fuel to not only achieve a cooling effect on high-temperature air, but also improve fuel utilization efficiency and avoid energy waste.

[0050] The spiral multi-fluid aviation pre-cooling heat exchanger described in the embodiment of the present invention is preferably suitable for multi-fluids, including dual-fluids, which is not specifically limited in the embodiment of the present invention.

[0051] The heat exchanger described in the embodiment of the present invention can be applied to high-temperature gas cooling in various application scenarios and has a very wide range of applications. The embodiment of the present invention does not specifically limit this.

[0052] In the embodiment of the present invention, the fuel introduced into the heat exchanger can be gasoline, diesel or various kerosene, or other types of hydrocarbon fuels, as long as the cooling purpose of the two-stage annular pre-cooling heat exchanger of the present invention can be achieved. In this regard, there is no specific limitation in the embodiment of the present invention.

[0053] Other embodiments of the present disclosure will readily occur to those skilled in the art after considering the specification and practicing the disclosure herein. This application is intended to cover any variations, uses, or adaptations of the present disclosure that follow the general principles of the present disclosure and include common knowledge or customary techniques in the art not disclosed herein. The description and examples are to be considered as exemplary only, with the true scope and spirit of the present disclosure being indicated by the following claims.

[0054] It should be understood that the present disclosure is not limited to the exact structures that have been described above and shown in the drawings, and that various modifications and changes can be made without departing from the scope thereof. The scope of the present disclosure is limited only by the appended claims.

Claims

1. A spiral multi-fluid aviation pre-cooling heat exchanger, characterized by: It includes a main cooling fuel cooling section and an auxiliary cooling fuel physical cooling section. The main cooling fuel cooling section is located outside the auxiliary cooling fuel physical cooling section. The main cooling fuel cooling section not only cools the high-temperature air by absorbing heat through high-temperature catalytic cracking of the main cooling fuel, but also cools the high-temperature air through physical absorption of heat by the main cooling fuel. The auxiliary cooling fuel physical cooling section cools the high-temperature air through physical absorption of heat by the auxiliary cooling fuel. The high-temperature air cooled by the heat exchanger passes through the main cooling fuel cooling section and the auxiliary cooling fuel physical cooling section in sequence, thereby achieving a cooling effect. The main cooling fuel cooling section comprises a main cooling fuel cooling section primary manifold outlet pipe (1), a main cooling fuel cooling section primary manifold inlet pipe (5), a plurality of main cooling fuel cooling section secondary manifold outlet pipes (2), a plurality of main cooling fuel cooling section secondary manifold inlet pipes (4) and a plurality of main cooling fuel cooling section spiral pipes (3); the main cooling fuel cooling section primary manifold outlet pipe (1) is located on the periphery of the main cooling fuel cooling section primary manifold inlet pipe (5); a plurality of main cooling fuel cooling section secondary manifold outlet pipes (2) are vertically arranged on the main cooling fuel cooling section primary manifold outlet pipe (1); a plurality of main cooling fuel cooling section secondary manifold inlet pipes (4) are vertically arranged on the main cooling fuel cooling section primary manifold inlet pipe (5); and the main cooling fuel cooling section spiral pipe (3) connects the main cooling fuel cooling section secondary manifold outlet pipe (2) and the main cooling fuel cooling section secondary manifold inlet pipe (4); The auxiliary cooling fuel physical cooling section comprises an auxiliary cooling fuel physical cooling section primary manifold water outlet pipe (6), an auxiliary cooling fuel physical cooling section primary manifold water inlet pipe (10), a plurality of auxiliary cooling fuel physical cooling section secondary manifold water outlet pipes (7), a plurality of auxiliary cooling fuel physical cooling section secondary manifold water inlet pipes (9), and a plurality of auxiliary cooling fuel physical cooling section spiral pipes (8). The auxiliary cooling fuel physical cooling section primary manifold water outlet pipe (6) is located at the auxiliary cooling fuel physical cooling section primary manifold water inlet pipe (10). On the periphery, a plurality of auxiliary cooling fuel physical cooling section secondary manifold water outlet pipes (7) are vertically arranged on the auxiliary cooling fuel physical cooling section primary manifold water outlet pipe (6), a plurality of auxiliary cooling fuel physical cooling section secondary manifold water inlet pipes (9) are vertically arranged on the auxiliary cooling fuel physical cooling section primary manifold water inlet pipe (10), and the auxiliary cooling fuel physical cooling section spiral pipe (8) connects the auxiliary cooling fuel physical cooling section secondary manifold water outlet pipe (7) and the auxiliary cooling fuel physical cooling section secondary manifold water inlet pipe (9).

2. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 1, characterized in that: The main cooling fuel cooling section spiral tube (3) and the auxiliary cooling fuel physical cooling section spiral tube (8) adopt Archimedean spirals.

3. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 1 or 2, characterized in that: The main cooling fuel cooling section spiral tube (3) and the auxiliary cooling fuel physical cooling section spiral tube (8) are arranged clockwise or counterclockwise.

4. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 3, characterized in that: The main cooling fuel cooling section spiral tube (3) is evenly arranged axially between the main cooling fuel cooling section secondary manifold water outlet pipe (2) and the main cooling fuel cooling section secondary manifold water inlet pipe (4).

5. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 3, characterized in that: The auxiliary cooling fuel physical cooling section spiral tube (8) is evenly arranged axially between the auxiliary cooling fuel physical cooling section secondary manifold water outlet pipe (7) and the auxiliary cooling fuel physical cooling section secondary manifold water inlet pipe (9).

6. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 1, characterized in that: The primary conduit outlet pipe (1) of the main cooling fuel cooling section, the primary conduit inlet pipe (5) of the main cooling fuel cooling section, the primary conduit outlet pipe (6) of the auxiliary cooling fuel physical cooling section, and the primary conduit inlet pipe (10) of the auxiliary cooling fuel physical cooling section are annular.

7. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 1, characterized in that: The main cooling fuel flows in from the primary manifold inlet pipe (5) of the main cooling fuel cooling section, and sequentially flows through the secondary manifold inlet pipe (4) of the main cooling fuel cooling section, the main cooling fuel cooling section spiral pipe (3), the secondary manifold outlet pipe (2) of the main cooling fuel cooling section, and the primary manifold outlet pipe (1) of the main cooling fuel cooling section, thereby cooling the high-temperature air through the main cooling fuel cooling section.

8. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 1 or 7, characterized in that: The auxiliary cooling fuel flows in from the auxiliary cooling fuel physical cooling section primary manifold water inlet pipe (10), and sequentially flows through the auxiliary cooling fuel physical cooling section secondary manifold water inlet pipe (9), the auxiliary cooling fuel physical cooling section spiral pipe (8), the auxiliary cooling fuel physical cooling section secondary manifold water outlet pipe (7), and the auxiliary cooling fuel physical cooling section primary manifold water outlet pipe (6), and cools the high-temperature air through the auxiliary cooling fuel physical cooling section.

9. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 1, characterized in that: The inner walls of the pipelines of the main cooling fuel cooling section are coated with a high-efficiency catalyst.

10. The spiral multi-fluid aviation pre-cooling heat exchanger according to claim 1, characterized in that: The plurality of secondary manifold outlet pipes (2) of the main cooling fuel cooling section are evenly arranged circumferentially on the primary manifold outlet pipe (1) of the main cooling fuel cooling section; the secondary manifold inlet pipes (4) of the main cooling fuel cooling section are evenly arranged circumferentially on the primary manifold inlet pipe (5) of the main cooling fuel cooling section; the plurality of secondary manifold inlet pipes (9) of the auxiliary cooling fuel physical cooling section are evenly arranged circumferentially on the primary manifold inlet pipe (10) of the auxiliary cooling fuel physical cooling section; the plurality of secondary manifold outlet pipes (7) of the auxiliary cooling fuel physical cooling section are evenly arranged circumferentially on the primary manifold outlet pipe (6) of the auxiliary cooling fuel physical cooling section.

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