Light annular titanium alloy heat dissipation device

Abstract

The utility model discloses a titanium alloy light annular heat dissipation device which is mainly composed of an annular heat dissipation core body, an exhaust funnel assembly and an installation support assembly, and the annular heat dissipation device is structurally used as an extension section of an airplane air inlet channel. The annular heat dissipation core assembly is made of light titanium alloy materials, the heat exchange fins are additionally arranged in the corrugated flow channels of the core assembly, so that the heat exchange area is increased in a limited space, the requirement for high-temperature (about 550 DEG C) air fluid is met, meanwhile, the heat exchange efficiency is kept at a high level, and the heat exchange efficiency is improved. The overall weight is greatly reduced compared with that of a stainless steel material, and the technical trend of lightweight design of airplanes is conformed.

Description

Technical Field

[0001] The utility model relates to a titanium alloy lightweight annular heat dissipation device, belonging to the field of aircraft environmental control and thermal management system design. Background Art

[0002] With the increasing demand for lightweight design of onboard equipment, the weight of the annular radiator, one of the cooling accessories of the aircraft environmental control and thermal management system, has always accounted for a large proportion of the weight of a single accessory. On the premise of meeting the requirements of heat exchange and flow resistance, a lightweight annular heat dissipation device that can meet the needs of high-temperature gas use and can significantly reduce weight is an urgent need for the development of current aircraft environmental control technology. Summary of the Invention

[0003] Considering that the highest temperature of the high-temperature air drawn from the engine in the environmental control system is often around 500°C, the materials that can meet this temperature range are generally stainless steel or high-temperature alloys. However, these materials have high density and are heavy. If aluminum alloy is used, although it has a lower density, currently mature and conventional aluminum alloys cannot be used in high-temperature conditions. For these reasons, the present utility model aims to provide a lightweight titanium alloy annular heat sink that can meet the system's need for significantly reducing the weight of accessories while maintaining good performance, and also provides a solution for cold air exhaust.

[0004] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0005] A titanium alloy lightweight annular heat dissipation device, comprising:

[0006] An annular heat dissipation core, wherein the annular heat dissipation core is mainly composed of a cylindrical bottom tube and a corrugated flow channel located on the outer wall of the bottom tube, a front ring is connected to an axial end face of the bottom tube, the front ring is conical, and the end with the smaller outer diameter of the conical front ring is connected to the bottom tube, the corrugated flow channel is a plurality of annular flow channels coaxial with the bottom tube, and the corrugated flow channel is divided into an inner layer corrugated flow channel and an outer layer corrugated flow channel that are not connected to each other, a plurality of air intake holes are opened on the bottom tube, which pass through the inner and outer walls of the bottom tube and are connected to the outer layer corrugated flow channel, the plurality of air intake holes are arranged at intervals along a direction parallel to the axis of the bottom tube, and each air intake hole is composed of a plurality of small holes distributed in a grid shape, an exhaust port is also provided on the outer layer corrugated flow channel, a heat exchange rib is provided in the inner layer corrugated flow channel, and one end of the heat exchange rib is connected to the outer wall of the bottom tube;

[0007] An exhaust pipe assembly, the exhaust pipe assembly is connected to the exhaust port on the outer corrugated flow channel through a flange structure to form a gas channel and extends in a direction away from the annular heat dissipation core;

[0008] The mounting bracket assembly is connected to the other axial end face of the base tube away from the front ring. The mounting bracket assembly mainly consists of a bracket and a mounting ring, wherein the bracket is an annular member with a flange edge, and one end of the bracket with the flange edge is connected to the base tube, and the other end of the bracket is connected to the mounting ring which also has a flange edge.

[0009] As a solution:

[0010] The front ring is connected to the bottom cylinder by resistance welding;

[0011] The mounting bracket assembly is connected to the bottom barrel by resistance welding;

[0012] The heat exchange fins are connected to the bottom cylinder by resistance welding.

[0013] As a solution:

[0014] The exhaust port includes a shell and an outlet nozzle. The shell covers the outer corrugated flow channel to form a space protruding toward the outside of the outer corrugated flow channel. A notch is opened on the surface of the shell, and the outlet nozzle is installed in the notch. A through hole for riveting is opened on the end surface of the outlet nozzle.

[0015] The exhaust pipe assembly includes a connecting flange and an exhaust pipe. A through hole is opened on the flange edge of the connecting flange, and one end with the through hole is riveted to the end face of the outlet nozzle with the riveting through hole, and the other end is welded to the exhaust pipe.

[0016] Furthermore, the annular heat dissipation core is wedge-connected to the connecting frame at the aircraft air inlet through the front ring.

[0017] As an option, the cross-section of the heat exchange fins includes but is not limited to L-shape, V-shape, U-shape or S-shape.

[0018] As an option, the heat exchange fins are provided with notches, and the shapes of the notches include but are not limited to rectangle, circle, triangle, polygon with five sides or more, V-shape or U-shape.

[0019] As a solution, the connecting flange further includes reinforcing ribs, which extend from the flange edge to near the connection between the connecting flange and the exhaust pipe.

[0020] Compared to existing technologies, this invention utilizes a titanium alloy, which is lighter than stainless steel or high-temperature alloys, to manufacture the annular heat dissipation core. Heat exchange fins are installed within the corrugated flow channel (the inner corrugated flow channel) to improve heat exchange efficiency. Furthermore, an exhaust pipe assembly is installed on the annular heat dissipation core, forming an air duct. This effectively discharges the gas exhausted from the annular heat dissipation core outside the aircraft, preventing it from escaping into the annular heat dissipation equipment compartment or other compartments, causing cabin temperatures to rise and affecting the normal operation of other cabin equipment. Furthermore, this invention significantly simplifies and reduces the weight of the mounting bracket assembly, ultimately meeting the aircraft environmental control system's requirements for efficient heat exchange and significant weight reduction of refrigeration accessories within a limited space. The weight reduction rate is expected to reach approximately 35%. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the structure of the titanium alloy lightweight annular heat dissipation device of the present invention;

[0022] Figure 2 for Figure 1 The main view;

[0023] Figure 3 for Figure 1 A top view of

[0024] Figure 4 for Figure 1 Left view of;

[0025] Figure 5 This is a schematic diagram of the connection structure between the front ring of the annular heat dissipation core, the heat exchange fins and the bottom tube;

[0026] Figure 6 Schematic diagram of the connection structure between the outlet nozzle and the shell;

[0027] Figure 7 Schematic diagram of the air duct on the bottom tube

[0028] Figure 8 Schematic diagram of the exhaust pipe assembly structure;

[0029] Figure 9 This is a schematic diagram of the mounting bracket assembly structure;

[0030] Figure 10 Schematic diagram of the heat exchange fin structure;

[0031] In the figure: 1-annular heat dissipation core, 2-exhaust pipe assembly, 3-mounting bracket assembly, 11-front ring, 12-bottom pipe, 13-heat exchange fins, 14-outlet nozzle, 15-housing, 16-rivet, 17-support plate nut, 18-corrugated flow channel, 21-connecting flange, 211-through hole, 212-reinforcement rib, 22-exhaust pipe, 31-bracket, 32-mounting ring, 33-rivet. DETAILED DESCRIPTION

[0032] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments. However, it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to common technical knowledge and customary means in the field are included in the scope of the present invention.

[0033] like Figures 1 to 4 As shown, the titanium alloy lightweight annular heat sink includes an annular heat sink core 1, an exhaust pipe assembly 2, and a mounting bracket assembly 3. The annular heat sink core 1 and the mounting bracket assembly 3 are connected by resistance welding, and the annular heat sink core 1 and the exhaust pipe assembly 2 are connected by screws. The three are assembled into an integral device. A large flow of aircraft external ram pressure cold air flows through the inner wall of the annular heat sink bottom barrel 12 through the air intake duct and enters the engine. As the large flow of cold air flows through the inner wall of the annular heat sink, it exchanges heat with the high-temperature air from the engine compressor. At the same time, due to the pressure difference between the inner wall bottom barrel 12 of the annular heat sink and the outside of the aircraft, a small portion of the large flow of cold air is introduced into the outer corrugated flow channel of the annular heat sink core assembly 1, and simultaneously exchanges heat with the high-temperature hot air in the inner corrugated flow channel, ultimately achieving the purpose of cooling the high-temperature hot air.

[0034] like Figure 5 As shown, the front end of the annular heat dissipation core 1 is a front ring 11, and the front ring 11 is connected to the bottom tube 12 by resistance welding. The front ring 11 is a conical surface with a taper α;

[0035] like Figure 5 As shown, there are two layers of corrugated flow channels 18 on the outside of the bottom tube 12 of the annular heat dissipation core 1, wherein the heat exchange fins 13 are connected to the bottom tube 12 by resistance welding in the inner layer of the corrugated flow channel, and the outer layer of the corrugated flow channel is welded to the outer surface of the inner layer of the corrugated flow channel. Figure 5 The inner layer corrugated flow channel and the outer layer corrugated flow channel are staggered by one corrugation in the axial direction of the bottom tube 12 .

[0036] like Figure 6 As shown, the outlet nozzle 14 on the annular heat dissipation core 1 is connected to the shell 15 by argon arc welding. A through hole for riveting is processed on the edge of the end flange of the outlet nozzle 14, and a rivet 16 is used to rivet the support plate nut 17 at the through hole for riveting.

[0037] like Figure 7 As shown, five mesh-shaped through holes are processed on the bottom tube 12 of the annular heat dissipation core 1 as air inlets, namely, air ducts, and each air duct consists of small holes distributed in a grid.

[0038] like Figure 8As shown, the exhaust pipe assembly 2 is formed by welding a connecting flange 21 and an exhaust pipe 22 together by argon arc welding, wherein a reinforcing rib 212 is provided on the connecting flange 21, and a through hole 211 for installation is processed between the reinforcing rib 212. The exhaust pipe assembly 2 is finally connected to the environment outside the machine. The exhaust pipe assembly 2 is similar to a circumferentially closed air duct. Without this air duct, the cold air cannot be directly discharged outside the machine after heat exchange and discharge from the annular diffuser core 1. The cold air will directly escape into the annular diffuser equipment compartment, or even enter the surrounding engine compartment or other compartments from the annular diffuser equipment compartment, causing the temperature in other compartments to rise, which is not conducive to the normal operation of the equipment in other compartments.

[0039] like Figure 9 As shown, the mounting bracket assembly 3 is composed of a bracket 31 and a mounting ring 32 riveted together by rivets 33, wherein mounting through holes are processed along the circumference of the bracket 31, so as to connect the mounting bracket assembly 3 to the frame on the aircraft.

[0040] like Figure 10 As shown, the cross-section of the heat exchange fin 13 is L-shaped, and circular through-holes are machined into the heat exchange fin 13. The above is only one specific embodiment of the present application, but the scope of protection of this application is not limited to this embodiment. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of this application. Therefore, the scope of protection of this application should be based on the scope of protection of the claims.

Claims

1. A titanium alloy lightweight annular heat sink, characterized in that: include: An annular heat dissipation core (1) is mainly composed of a cylindrical bottom tube (12) and a corrugated flow channel (18) located on the outer wall of the bottom tube (12); a front ring (11) is connected to an axial end face of the bottom tube (12); the front ring (11) is conical, and the end with the smaller outer diameter of the conical front ring (11) is connected to the bottom tube (12); the corrugated flow channel (18) is a plurality of annular flow channels coaxial with the bottom tube (12), and the corrugated flow channel (18) is divided into mutually unconnected The bottom tube (12) is provided with a plurality of air inlet holes penetrating the inner and outer walls of the bottom tube (12) and communicating with the outer corrugated flow channel. The plurality of air inlet holes are spaced apart in a direction parallel to the axis of the bottom tube (12). Each air inlet hole is composed of a plurality of small holes distributed in a grid shape. An exhaust port is also provided on the outer corrugated flow channel. A heat exchange fin (13) is provided in the inner corrugated flow channel. One end of the heat exchange fin (13) is connected to the outer wall of the bottom tube (12). An exhaust pipe assembly (2), wherein the exhaust pipe assembly (2) is connected to the exhaust port on the outer corrugated flow channel via a flange structure to form a gas channel and extends in a direction away from the annular heat dissipation core (1); The mounting bracket assembly (3) is connected to the other axial end face of the bottom cylinder (12) away from the front ring (11). The mounting bracket assembly (3) mainly consists of a bracket (31) and a mounting ring (32), wherein the bracket (31) is an annular member with a flange edge, and one end of the bracket (31) with the flange edge is connected to the bottom cylinder (12), and the other end of the bracket (31) is connected to the mounting ring (32) also with a flange edge.

2. The titanium alloy lightweight annular heat sink according to claim 1, characterized in that: The front ring (11) and the bottom cylinder (12) are connected by resistance welding; The mounting bracket assembly (3) is connected to the bottom cylinder (12) by resistance welding; The heat exchange fins (13) are connected to the bottom cylinder (12) by resistance welding.

3. The titanium alloy lightweight annular heat sink according to claim 1, characterized in that: The exhaust port comprises a shell (15) and an outlet nozzle (14). The shell (15) covers the outer corrugated flow channel to form a space protruding toward the outer side of the outer corrugated flow channel. A notch is provided on the surface of the shell (15). The outlet nozzle (14) is installed in the notch. A through hole for riveting is provided on the end surface of the outlet nozzle (14). The exhaust pipe assembly (2) comprises a connecting flange (21) and an exhaust pipe (22). A through hole (211) is provided on the flange edge of the connecting flange (21), and one end with the through hole (211) is riveted to the end face of the outlet nozzle (14) with the through hole for riveting, and the other end is welded to the exhaust pipe (22).

4. The titanium alloy lightweight annular heat sink according to claim 1, characterized in that: The annular heat dissipation core (1) is wedge-connected to a connecting frame at an aircraft air inlet via a front ring (11).

5. The titanium alloy lightweight annular heat sink according to claim 1, characterized in that: The cross-section of the heat exchange fin (13) includes but is not limited to an L-shape, a V-shape, a U-shape or an S-shape.

6. The titanium alloy lightweight annular heat sink according to claim 1, characterized in that: The heat exchange fins (13) are provided with notches, and the shapes of the notches include but are not limited to rectangle, circle, triangle, polygon with five sides or more, V-shape or U-shape.

7. The titanium alloy lightweight annular heat sink according to claim 3, characterized in that: The connecting flange (21) further comprises a reinforcing rib (212), which extends from the flange edge to the vicinity of the connection between the connecting flange (21) and the exhaust pipe (22).

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