Heat exchanger of aircraft environment control system

Abstract

The utility model discloses a heat exchanger of an aircraft environment control system, which is characterized in that an injection device is integrated at a cold side outlet of the heat exchanger, when in high altitude, ram air is introduced from an outer duct of an engine as a cold source to flow through a cold side channel to exchange heat with high-temperature and high-pressure air flowing through a hot side channel, and the ram air is used for cooling the high-temperature air; on the ground, a part of high-temperature and high-pressure air forms high-speed jet flow under the action of a nozzle of the injection assembly, and ambient air is injected under the suction action generated by the pressure difference between exhaust pressure and ambient pressure, so that low-temperature air flows through the cold side channel and exchanges heat with the high-temperature and high-pressure air flowing through the hot side channel; and the aircraft can still cool high-temperature air when no ram air exists on the ground. According to the utility model, high-temperature air from an engine is cooled to a proper temperature through stamping or injected air, so that the air can be used by a downstream air system. According to the utility model, the aircraft environment control system can be normally used at high altitude and on the ground.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of the heat management system design of airplane engine and environmental control, especially a heat exchanger of airplane environmental control system. BACKGROUND

[0002] When the airplane rises from the ground to high altitude, the environmental condition of outside changes very sharply, the atmospheric pressure of outside can change from one atmosphere to near vacuum, and the temperature will also drop sharply, in order to ensure the normal life of passengers and air crew and the reliable work of equipment during flight, the cabin and equipment cabin of modern airplane need to be controlled.

[0003] The air circulation system of airplane generally uses the air led by main engine as supply air, but the temperature of air is high at this time, and the air cannot be directly used in subsequent environmental control system, therefore, the pre-cooler needs to be used to reduce the temperature of engine bleed air, the pre-cooler is a kind of heat exchanger, as an important part of airplane environmental control system, is generally divided into plate-fin type, tube-in-tube type, shell-and-tube type and the like, and high-altitude ram air is generally used as cold source to exchange heat with engine bleed air in the heat exchanger to reduce the temperature of engine bleed air.

[0004] When the airplane is not taking off on the ground, the environmental control system still needs to work to maintain the life of personnel and the safe operation of equipment, but at this time, due to the lack of high-altitude ram air as cold source, other cold sources need to be used to pre-cool the engine bleed air. SUMMARY

[0005] The utility model aims at providing a kind of heat exchanger of airplane environmental control system, for airplane environmental control system, make airplane when high altitude and ground its environmental control system can be normally used, it is compact, light and has lower energy consumption.

[0006] To achieve the above object, the utility model adopts the following technical scheme:

[0007] The heat exchanger of airplane environmental control system includes:

[0008] The core subassembly is plate-fin type heat exchange structure, and includes sealed hot side channel and cold side channel which are arranged in cross and independent of each other;

[0009] The hot side inlet and outlet assembly includes hot side inlet assembly and hot side outlet assembly, wherein the hot side inlet assembly is communicated with the inlet of hot side channel, and the hot side outlet assembly is communicated with the outlet of hot side channel;

[0010] The cold side inlet and outlet assembly includes cold side inlet assembly and cold side outlet assembly, wherein the cold side inlet assembly is communicated with the inlet of cold side channel, and the cold side outlet assembly is communicated with the outlet of cold side channel;

[0011] An ejector assembly is arranged on the cold side outlet assembly, an air intake end of the ejector assembly is connected to high-temperature and high-pressure air from an aircraft engine, and a gas flow injection end of the ejector assembly is connected to the atmosphere.

[0012] Further,

[0013] The hot side inlet assembly comprises a hot side inlet joint and a hot side inlet end cover, the hot side inlet end cover is arranged between the inlet of the hot side channel and the hot side inlet joint, the hot side inlet joint is a female joint, and the hot side inlet end cover is a circular arc transition structure, the cross section of the hot side inlet end cover gradually decreases from the inlet of the hot side channel to the hot side inlet joint.

[0014] The hot side outlet assembly comprises a hot side outlet joint and a hot side outlet end cover, the hot side outlet end cover is arranged between the outlet of the hot side channel and the hot side outlet joint, the hot side outlet joint is a male joint, and the hot side outlet end cover is a circular arc transition structure, the cross section of the hot side outlet end cover gradually decreases from the outlet of the hot side channel to the hot side outlet joint.

[0015] Further,

[0016] One end of the hot side inlet end cover connected to the hot side inlet joint comprises a straight edge, and one end of the hot side inlet end cover connected to the inlet of the hot side channel also comprises a straight edge.

[0017] One end of the hot side outlet end cover connected to the hot side outlet structure comprises a straight edge, and one end of the hot side outlet end cover connected to the outlet of the hot side channel also comprises a straight edge.

[0018] Further,

[0019] The cold side inlet assembly comprises a cold side inlet end cover and a cold side inlet flange, the cold side inlet end cover is arranged between the cold side inlet flange and the inlet of the cold side channel, the flange surface of the cold side inlet flange is at an acute angle with the windward surface, and the cold side inlet end cover is a circular arc transition structure, the cross section of the cold side inlet end cover gradually decreases from the inlet of the cold side channel to the cold side inlet flange.

[0020] The cold side outlet assembly comprises a cold side outlet end cover and a cold side outlet flange, the cold side outlet end cover is arranged between the cold side outlet flange and the outlet of the cold side channel, the flange surface of the cold side outlet flange is perpendicular to the windward surface, and the cold side outlet end cover is a circular arc transition structure, the cross section of the cold side outlet end cover gradually decreases from the outlet of the cold side channel to the cold side outlet flange.

[0021] As an option, an ejector assembly is arranged between the cold side outlet end cover and the cold side outlet flange, and the ejector assembly comprises:

[0022] A ring pipe, which is a circumferentially closed annular pipe, the inner cavity of the annular pipe forms a gas flow channel, the axial first end of the annular pipe is connected to the cold side outlet flange, and the axial second end is connected to the cold side outlet end cover.

[0023] The nozzle is uniformly distributed along the inner ring surface of the ring pipe, and the nozzle is a Laval nozzle structure.

[0024] The injection inlet flange is arranged on the outer ring surface of the ring pipe, and the injection inlet of the injection inlet flange introduces high-temperature and high-pressure air from the aircraft engine.

[0025] Further, the jet direction of the exhaust end of the nozzle is parallel to the axial direction of the ring pipe.

[0026] Further, the core subassembly is further provided with a mounting seat on one end face.

[0027] As an option:

[0028] The core subassembly is mainly composed of fins, seals, partitions and side plates, and the fins corresponding to the hot side channel and the cold side channel are wave-shaped fins.

[0029] The hot side inlet and outlet assembly and the cold side inlet and outlet assembly are welded on different end faces of the core subassembly by argon arc welding.

[0030] The working principle of the heat exchanger is that the high-temperature and high-pressure hot air introduced by the engine is evenly introduced into the core subassembly hot side flow channel through the hot side inlet after rectification, and the low-temperature air is subjected to convection heat exchange. The heat of the high-temperature air is transmitted to the low-temperature air through the fins and the partitions, the fins can increase the heat exchange area while increasing the disturbance and improving the heat exchange efficiency, and the plate-fin heat exchanger adopted by the utility model has high compactness, light weight and high efficiency.

[0031] Compared with the prior art, the heat exchanger integrated with the injection device combines the heat exchanger with the ejector, and when the aircraft works on the ground, the normal-temperature atmosphere can be sucked through the cold side channel of the heat exchanger by the injection device, the high-temperature and high-pressure air from the engine flowing through the hot side channel is subjected to heat exchange, and the injection inlet air flow is also the high-temperature and high-pressure air from the engine. The high-temperature and high-pressure air is mixed and exchanged with the air at the cold side outlet of the heat exchanger at the nozzle outlet of the ejector, so as to reduce the temperature of the engine bleed air, and the structure is compact and light in weight, and the aircraft environmental control system can work normally on the ground.

[0032] The utility model discloses a low-temperature air is introduced by the engine outer duct at high altitude, enters the core subassembly cold edge flow channel and the high-temperature high-pressure air that flows through the hot edge channel after rectifying through the cold edge import, and the temperature of the high-temperature high-pressure air from the engine is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0033] Figure 1 It is the structure schematic drawing of the utility model;

[0034] Figure 2 It is the structure schematic drawing of the core subassembly of the utility model;

[0035] Figure 3 It is the structure schematic drawing of the hot edge import and export subassembly of the utility model;

[0036] Figure 4 It is the schematic diagram of the cold edge import and export subassembly and the ejector assembly of the utility model;

[0037] Figure 5 It is the structure schematic drawing of the ejector assembly of the utility model;

[0038] Figure 6 It is the structure schematic drawing of the nozzle of the utility model;

[0039] Figure 7 It is the installation schematic drawing of the mounting seat of the utility model;

[0040] In the drawing: 1. core subassembly;2. hot edge import and export subassembly;3. cold edge import and export subassembly;4. ejector assembly;5. mounting seat. DETAILED DESCRIPTION

[0041] The utility model will be further explained below in conjunction with the attached drawing and specific embodiment, but should not be understood as the range of the subject matter described in the utility model is limited to the following embodiment, and under the condition of not departing from the above technical thought of the utility model, all kinds of modifications, replacement and change according to the ordinary technical knowledge and conventional means in the art are included in the range of the utility model.

[0042] As Figures 1-7The utility model discloses a heat exchanger integrated structure with an ejector device, which mainly comprises a core subassembly 1, a hot side inlet and outlet assembly 2, a cold side inlet and outlet assembly 3, an ejector assembly 4 and a mounting seat 5.

[0043] The core subassembly 1 is of a plate-fin structure and is divided into a cold side and a hot side, which are composed of fins, sealing strips, partitions, brazing filler metals and side plates, and the cold side and the hot side are both of wave-shaped fins. The core subassembly 1 is a sealed passage for cold and hot media, and the cold and hot passages are independently arranged in a cross manner, so that the high-temperature air from an engine and the low-temperature ram air or the ejector air can fully exchange heat through the heat exchange surfaces such as the partitions and the fins, thereby reducing the temperature of the high-temperature air to supply an aircraft environmental control system.

[0044] The hot side inlet assembly 2 comprises a hot side inlet joint, a hot side outlet joint, a hot side inlet end cover and a hot side outlet end cover. The hot side inlet joint is in the form of a female joint, and the hot side outlet joint is in the form of a male joint. The hot side inlet end cover and the hot side outlet end cover are transition parts between the core subassembly 1 and pipelines, which mainly serve to collect air and guide flow and also serve to seal and bear pressure. Therefore, the hot side inlet end cover and the hot side outlet end cover are both designed to have a circular arc transition structure, which not only improves the pressure-bearing performance of the structure but also allows the air flow to be fully mixed. In order to improve the welding quality, straight edge segments are designed at the inlets and outlets of the hot side inlet end cover and the hot side outlet end cover.

[0045] The cold side inlet and outlet assembly 3 comprises a cold side inlet end cover, a cold side outlet end cover, a cold side inlet flange and a cold side outlet flange. The cold side inlet end cover and the cold side outlet end cover are also designed to have a circular arc transition structure. The cold side inlet and outlet are connected by flanges. The flange surface of the cold side inlet flange forms a 60° angle with the windward surface, and the flange surface of the cold side outlet flange is perpendicular to the windward surface. Meanwhile, the cold side outlet flange is connected to the ejector assembly 4. When the aircraft is on the ground, the ejector air and the high-temperature and high-pressure air are used to exchange heat, thereby ensuring that the environmental control system of the aircraft works normally on the ground.

[0046] The ejector assembly 4 comprises a ring pipe, a nozzle and an ejector inlet flange. The ejector assembly 4 is connected between the cold side outlet end cover and the cold side outlet flange. The nozzle is of a Laval nozzle structure, that is, the inner diameter of the front half of the nozzle is gradually reduced to a narrow throat in the middle, and then gradually expanded outward after the narrow throat, so that the gas can be continuously accelerated to form a pressure difference in the cold side inlet and outlet, thereby generating the ejector air. The inlet of the ejector assembly 4 is connected by a flange.

[0047] The mounting seat 5 is made of a high-temperature alloy and is mounted and welded on the core body assembly 1.

[0048] The heat exchanger mainly employs welding and machining processes. The core assembly 1 uses vacuum brazing to weld components such as fins, seals, baffles, brazing filler metal, and side plates into a whole. The remaining components are welded using argon arc welding. The cold-side inlet and outlet end caps, the hot-side inlet and outlet end caps, and the mounting base 5 are welded onto the core assembly.

[0049] At high altitudes, the high-temperature, high-pressure gas drawn from the engine enters the hot-side channel of core assembly 1 after being rectified by the hot-side inlet connector and hot-side inlet end cover. Heat is transferred to the cold-side fluid via fins and baffles, and the gas then flows out of the heat exchanger through the hot-side outlet end cover. At high altitudes, ram air is drawn from the engine's outer bypass duct as a cold source, flowing into the cold-side channel of core assembly 1 after being rectified by the cold-side inlet flange and cold-side inlet end cover, where it exchanges heat with the high-temperature, high-pressure air flowing through the hot-side channel. At ground level, a portion of the high-temperature, high-pressure gas enters the hot-side channel of core assembly 1 after being rectified by the hot-side inlet connector and hot-side inlet end cover. Heat is transferred to the cold-side fluid via fins and baffles, and the gas then flows out of the heat exchanger through the hot-side outlet end cover. Another portion of the high-temperature, high-pressure gas flows into the ring pipe via the ejector inlet flange, expands and accelerates through the nozzle to form a high-speed jet. The suction effect generated by the pressure difference between the exhaust pressure and the ambient pressure is used to eject ambient air, allowing low-temperature air to flow through the cold-side channel of core assembly 1 and exchange heat with the high-temperature, high-pressure air flowing through the hot-side channel.

[0050] like Figure 2 The diagram shows the structure of core assembly 1. The core assembly is a plate-fin heat exchanger, which is made of fins, seals, baffles, brazing filler metal and side plates by vacuum brazing. Both the hot and cold sides are wavy fins, and the flow pattern is crossflow. Its hot and cold channels are arranged independently and cross each other, so that the high-temperature air from the engine and the low-temperature ram air or ejector air can fully exchange heat through the heat transfer surfaces such as baffles and fins.

[0051] like Figure 3 As shown, the hot-edge inlet / outlet assembly 2 includes a hot-edge inlet connector, a hot-edge outlet connector, a hot-edge inlet end cap, and a hot-edge outlet end cap. The hot-edge inlet connector is a concave connector, and the hot-edge outlet connector is a convex connector. The hot-edge inlet end cap and the hot-edge outlet end cap are transition parts between the core assembly 1 and the pipeline, serving to collect and guide airflow, as well as to seal and bear pressure. The hot-edge inlet end cap and the hot-edge outlet end cap are designed with a rounded transition structure, which improves the pressure bearing performance of the structure and allows the airflow to mix fully. At the same time, in order to improve the welding quality, an 8mm straight edge section is designed at the inlet and outlet of the hot-edge inlet end cap and the hot-edge outlet end cap.

[0052] like Figure 4As shown, the cold edge import and export assembly 3 and the injection assembly 4, the cold edge import end cover and the cold edge export end cover are designed as a circular arc transition structure; the cold edge import and export adopts flange connection, the flange face of the cold edge import flange is 60° included angle with the windward surface, the flange face of the cold edge export flange is perpendicular to the windward surface; meanwhile, the injection assembly 4 is connected between the cold edge export flange and the cold edge export end cover.

[0053] As shown in Figure 5 , Figure 6 As shown, the injection assembly 4 and the structure diagram of the injection nozzle, including the ring pipe, the nozzle and the injection import flange, the nozzle is the structure of the Laval nozzle, the front half of the Laval nozzle is contracted to a throat pipe by big to small to the middle, the throat pipe is expanded outward by small to big after the throat pipe, the high pressure gas flows into the front half of the nozzle, and is sprayed out by the rear half after passing through the throat pipe. When the gas enters the nozzle contraction section, the gas movement follows the principle that "the flow velocity is large in the small section and the flow velocity is small in the large section when the fluid moves in the pipe", so the gas flow is continuously accelerated, and the flow velocity is from subsonic to sonic. When reaching the narrow throat, the flow velocity exceeds the sonic speed, at this time the gas movement follows the principle that "the larger the section, the faster the flow velocity", so in the nozzle expansion section, the velocity of the gas is further accelerated until the velocity is accelerated to supersonic, the high-speed fluid is sprayed to produce thrust, and the suction effect generated by the pressure difference between the exhaust pressure and the environment pressure is used to realize the injection of the environment air.

[0054] As shown in Figure 7 As shown, the mounting seat 5 is welded on the core assembly 1 by argon arc welding process.

[0055] The above embodiments are not used to limit the protection scope of the present application, and any deformation, modification or equivalent replacement made on the basis of the technical scheme of the present application shall fall within the protection scope of the present application.

Claims

1. Heat exchanger for an aircraft environmental control system, characterized in that It comprises: a core subassembly (1) which is a plate-fin heat exchange structure and contains sealed hot-side and cold-side channels arranged in cross and independent of each other; a hot-side inlet and outlet subassembly (2) which contains a hot-side inlet subassembly and a hot-side outlet subassembly, wherein the hot-side inlet subassembly is in communication with the inlet of the hot-side channel and the hot-side outlet subassembly is in communication with the outlet of the hot-side channel; a cold-side inlet and outlet subassembly (3) which contains a cold-side inlet subassembly and a cold-side outlet subassembly, wherein the cold-side inlet subassembly is in communication with the inlet of the cold-side channel and the cold-side outlet subassembly is in communication with the outlet of the cold-side channel; an injection subassembly (4) which is arranged on the cold-side outlet subassembly, the air inlet end of the injection subassembly (4) is arranged to introduce high-temperature and high-pressure air from an aircraft engine, and the air flow jet end of the injection subassembly (4) is in communication with the atmospheric environment.

2. The aircraft environmental control system heat exchanger according to claim 1, wherein: the hot-side inlet subassembly comprises a hot-side inlet joint and a hot-side inlet end cover, the hot-side inlet end cover is arranged between the inlet of the hot-side channel and the hot-side inlet joint, wherein the hot-side inlet joint is a female joint, and the hot-side inlet end cover is a circular arc transition structure, the cross section of which gradually decreases from the inlet of the hot-side channel to the hot-side inlet joint; the hot-side outlet subassembly comprises a hot-side outlet joint and a hot-side outlet end cover, the hot-side outlet end cover is arranged between the outlet of the hot-side channel and the hot-side outlet joint, wherein the hot-side outlet joint is a male joint, and the hot-side outlet end cover is a circular arc transition structure, the cross section of which gradually decreases from the outlet of the hot-side channel to the hot-side outlet joint.

3. The aircraft environmental control system heat exchanger according to claim 1, wherein: one end of the hot-side inlet end cover connected with the hot-side inlet joint comprises a straight edge, and one end of the hot-side channel connected with the hot-side inlet end cover also comprises a straight edge; one end of the hot-side outlet end cover connected with the hot-side outlet structure comprises a straight edge, and one end of the hot-side channel connected with the hot-side outlet end cover also comprises a straight edge.

4. The aircraft environmental control system heat exchanger according to claim 1, wherein: the cold-side inlet subassembly comprises a cold-side inlet end cover and a cold-side inlet flange, the cold-side inlet end cover is arranged between the cold-side inlet flange and the inlet of the cold-side channel, wherein the flange surface of the cold-side inlet flange forms an acute angle with the windward surface, and the cold-side inlet end cover is a circular arc transition structure, the cross section of which gradually decreases from the inlet of the cold-side channel to the cold-side inlet flange; the cold-side outlet subassembly comprises a cold-side outlet end cover and a cold-side outlet flange, the cold-side outlet end cover is arranged between the cold-side outlet flange and the outlet of the cold-side channel, wherein the flange surface of the cold-side outlet flange is perpendicular to the windward surface, and the cold-side outlet end cover is a circular arc transition structure, the cross section of which gradually decreases from the outlet of the cold-side channel to the cold-side outlet flange.

5. An aircraft environmental control system heat exchanger as claimed in claim 4, characterised in that: the injection subassembly (4) is arranged between the cold-side outlet end cover and the cold-side outlet flange, and the injection subassembly (4) comprises: a ring pipe which is a circumferentially closed annular pipe, the inner cavity of the annular pipe forms a gas flow channel, the axial first end of the annular pipe is connected with the cold-side outlet flange, and the axial second end is connected with the cold-side outlet end cover; The nozzles are uniformly distributed along the inner ring surface of the ring pipe at equal central angles, the nozzles are in the structure of Laval nozzle, the air inlet end of the nozzles is communicated with the inner cavity of the ring pipe, and the air outlet end of the nozzles is communicated with the atmosphere; The injection inlet flange is arranged on the outer ring surface of the ring pipe, the injection inlet of the injection inlet flange introduces high-temperature and high-pressure air from the aircraft engine, and the outlet of the injection inlet flange is communicated with the inner cavity of the ring pipe.

6. The aircraft environmental control system heat exchanger of Claim 5, wherein: The air flow injection direction of the air outlet end of the nozzles is parallel to the axial direction of the ring pipe.

7. The aircraft environmental control system heat exchanger of claim 1, wherein: An installation seat (5) is further arranged on one end surface of the core subassembly (1).

8. The aircraft environmental control system heat exchanger according to claim 1, characterized in that: The core subassembly (1) is mainly composed of fins, sealing strips, partition plates and side plates and is vacuum brazed, the fins corresponding to the hot side channel and the cold side channel are wave-shaped fins, and the hot side channel and the cold side channel are arranged in the cross-flow form; The hot side inlet and outlet assembly (2) and the cold side inlet and outlet assembly (3) are welded on different end surfaces of the core subassembly (1) through argon arc welding.

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