CN115597419B - Precooler for aircraft engine - Google Patents

Abstract

The present application provides a precooler for an aero-engine, which includes two annular header parts and a plurality of heat exchange assemblies, each heat exchange assembly includes a first mounting plate and a second mounting plate; the first mounting plate Both the plate and the second mounting plate are provided with hollow cavities, and a plurality of microtubes are connected between the first mounting plate and the second mounting plate, and the two ends of each microtube are connected with the first mounting plate and the second mounting plate respectively. The hollow cavity on the top is connected; among them, a gap for air circulation is formed between a plurality of microtubes; among them, a plurality of heat exchange components are assembled between two header parts, and the first part of each heat exchange component after assembly The mounting plate and the second mounting plate intersect two header parts; wherein, each header part is provided with a plurality of working medium flow holes communicating with the hollow cavity of each heat exchange assembly. The precooler provided by the invention simultaneously solves the problems of flow-induced vibration of the heat exchange tube, difficulty in welding and assembling the heat exchange component, and high maintenance cost.

Description

A precooler for aero-engine

technical field

The present application relates to the field of cooling equipment for aero-engines, in particular to a precooler for aero-engines.

Background technique

The hypersonic strong pre-cooling engine can be used as a power system for horizontal take-off and landing and repeated use of aerospace vehicles. It can start from Mach 0 and perform high-performance navigation in the range of Mach 0 to Mach 6. It is a very important new type in the field of aerospace technology. powerplant. Relevant data show that when flying at Mach 5, the temperature of the airflow entering the engine after deceleration can reach above 1000°C. High intake air temperature not only deteriorates the material performance and reliability of the engine, but also reduces the compressibility of the air and reduces the power. The performance of the system drops sharply, making it difficult to meet the thrust requirements of aerospace vehicles. One of the existing technical solutions is to reduce the temperature of the airflow by installing a precooler in the air inlet, thereby improving the working environment of the engine and satisfying the power performance of the aircraft at a high Mach number.

Most of the existing precooler structures are microtube-bundle heat exchangers, which use high-temperature air to sweep across a large number of microtube bundles to exchange heat with the cooling fluid flowing inside the microtubes. Compared with the traditional tube-bundle heat exchanger, the micro-tube-bundle heat exchanger has higher compactness and better heat exchange capacity, but it has the following new problems:

1. The length of the microtube is long, which is prone to strong flow-induced vibration. In severe cases, the heat transfer tube will be damaged, which will affect the heat transfer performance and operation safety of the precooler;

2. The microtubes usually change according to a certain curvature along the length of the tube. Due to the extremely compact requirements of the precooler, it is difficult to guarantee the installation accuracy of tens of thousands of microtube bundles during the welding process, and the welding assembly is difficult. high;

3. The structure of the coolant side or the air side of the traditional precooler is an integrated design. When the heat exchange component is damaged, the entire precooler needs to be replaced, and the maintenance cost is high.

Contents of the invention

In view of the above problems, the present invention provides a precooler for aero-engines, which solves the flow-induced vibration of the heat exchange tubes and the difficulty in welding and assembling the heat exchange components by modularizing the heat exchange components into the main body of the precooler large size and high maintenance costs.

Technical scheme of the present invention is:

A precooler for an aero-engine, comprising two annular header parts and a plurality of heat exchange assemblies, each heat exchange assembly includes a first mounting plate and a second mounting plate;

Both the first mounting plate and the second mounting plate are provided with hollow cavities, and a plurality of microtubes are connected between the first mounting plate and the second mounting plate, and each of the two ends of the microtubes communicate with the hollow cavities on the first mounting plate and the second mounting plate respectively; wherein, a gap for air to circulate from the outside to the inside is formed between the plurality of microtubes;

Wherein, a plurality of said heat exchanging assemblies are assembled between two said header parts, and said first mounting plate and said second mounting plate of each heat exchanging assembly after assembly are connected with two said headers parts intersect;

Wherein, each of the header parts is provided with a plurality of working medium flow holes communicating with the hollow cavity of each heat exchange component, and the cooling working fluid flows into the hollow cavity through the working medium flow holes, and passes through the hollow cavity. The hollow cavity flows into the micropipe to cool the air circulating in the gap.

Optionally, one of the header parts has a shunt pipe, and the other header part is provided with a header;

The shunt pipe is provided with a plurality of shunt holes communicating with the hollow cavity on the first mounting plate;

The collecting pipe is provided with a plurality of collecting holes communicating with the hollow cavity on the second mounting plate;

Wherein, the cooling medium flows into the hollow cavities on the first mounting plate from the plurality of distribution holes, flows into the microtubes through the corresponding hollow cavities, and flows from the microtubes It flows into the hollow cavity on the second mounting plate, and flows out of the hollow cavity through a plurality of collecting holes.

Optionally, the distribution pipes and the header pipes are respectively arranged on the inner ring edge or the outer ring edge of the corresponding header part.

Optionally, a shunt pipe and a collector pipe are arranged on the two header parts;

One of the header components is provided with a first distribution pipe and a first collection pipe, and the first distribution pipe is provided with a plurality of distribution holes communicating with the hollow cavity on the first mounting plate and the first distribution pipe. A header is provided with a plurality of header holes communicating with the hollow cavity on the first mounting plate;

The other manifold part is provided with a second branch pipe and a second manifold; the second branch pipe is provided with a plurality of branch holes communicating with the hollow cavity on the second mounting plate and the The second header is provided with a plurality of header holes communicating with the hollow cavity on the second mounting plate;

Each of the hollow cavities is divided into a plurality of first regions and a plurality of second regions; wherein,

The first branch pipe, the second header pipe, and the corresponding microtubes in the first region form a first cooling channel;

The second branch pipe, the first header pipe, and the corresponding microtubes in the second area form a second cooling channel;

The flow directions of the cooling medium in the first cooling channel and the second cooling channel are opposite.

Optionally, both the first manifold and the second manifold are disposed on the inner ring edge of the corresponding manifold component, and both the first manifold and the second manifold are disposed on the outer ring edge of the corresponding said header part; or,

The first manifold and the second header are arranged on the inner ring edge of the corresponding header part, and the second manifold and the first header are arranged on the corresponding collector. on the outer ring edge of the pipe part.

Optionally, a plurality of U-shaped splitter plates are arranged in the hollow cavity, and the plurality of U-shaped splitter plates are arranged in a staggered manner between both sides of the hollow cavity, so that the The microtubes are divided into microtubes in the first region and microtubes in the second region.

Optionally, the cross-sections of the distribution pipe and the collection pipe are circular segments.

Optionally, at least one partition is connected between the first mounting plate and the second mounting plate, and the partition is spaced between the plurality of microtubes.

Optionally, a plurality of ventilation holes are scattered on the separator.

Compared with the prior art, the present application includes the following advantages:

The present invention proposes a precooler for an aero-engine, comprising two annular header parts and a plurality of heat exchange assemblies, each heat exchange assembly includes a first mounting plate and a second mounting plate; the first mounting plate Hollow cavities are arranged on the second mounting plate and the second mounting plate, and a plurality of microtubes are connected between the first mounting plate and the second mounting plate, and the two ends of each microtube are connected with the first mounting plate and the second mounting plate respectively. The hollow cavity communicates with each other; among them, a gap for air to circulate from outside to inside is formed between a plurality of microtubes; among them, a plurality of heat exchange components are assembled between two header parts, and each heat exchange component after assembly The first mounting plate and the second mounting plate intersect with two header parts; wherein, each header part is provided with a plurality of working fluid flow holes communicating with the hollow cavity of each heat exchange component, and the cooling working fluid passes through The working fluid flow hole flows into the hollow cavity, and flows into the micropipe through the hollow cavity, so as to cool the air circulating in the gap.

By adopting the technical solution of this application, two mounting plates and a hollow cavity form the main structure of the heat exchange assembly, and a plurality of heat exchange assemblies are assembled on the circular header part to form a modular precooler, which has at least the following Several notable improvements:

1. In the embodiment of the present invention, the required length of the microtubes installed on the two mounting plates on each heat exchange component is relatively short, and the rigidity of the short tubes is better, which greatly weakens the flow-induced vibration caused by the air swept outside the tube bundle Strength, good anti-vibration effect can be achieved without adding additional support structures;

2. The structure of the heat exchange component in the embodiment of the present invention can be matched with the micro straight tube, and the micro tube is directly welded to the two mounting plates, which improves the strength and safety of the welding position, and makes the welding and assembly process easier;

3. The multiple heat exchange components in the embodiment of the present invention are independent and cooperate with each other, and the air enters multiple heat exchange components at the same time to enhance heat exchange. When the precooler is damaged, only the damaged heat exchange component needs to be replaced , low maintenance cost;

4. A plurality of heat exchange components in the embodiment of the present invention are arranged in the circumferential direction and welded to form a sleeve-shaped heat exchange structure. The microtubes on each heat exchange component are laid between the two mounting plates in the circumferential direction, and the whole end-to-end contact A number of ring-shaped micro-tube layers are formed from the inner wall of the casing to the outer wall of the casing, the micro-tubes are more compact, and the contact area between the micro-tubes and the air increases, and the overall heat transfer capacity is significantly improved;

5. In the embodiment of the present invention, when a plurality of heat exchange components are assembled between two circular header parts, it is only necessary to change the assembly direction of the heat exchange components to form a sleeve-shaped heat exchanger with microtubes as the tube wall surface as a whole. The thermal structure ensures all-round cooling of the air entering from around the tube wall. The micro tubes only need to be welded according to the vertical distance between the two mounting plates, and there is no need to maintain the concentricity between the micro tubes in multiple heat exchange components during welding. The degree greatly reduces the difficulty of welding assembly;

6. A plurality of heat exchange components in the embodiment of the present invention are connected to the header components, and by changing the parameters of each heat exchange component, it is possible to realize the control of the flow distribution of the cooling medium at a local position, which is more flexible and realizes the improvement of the overall Uniformity of heat transfer.

Description of drawings

In order to illustrate the technical solution of the present application more clearly, the accompanying drawings that need to be used in the description of the present application will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. Ordinary technicians can also obtain other drawings based on these drawings without paying creative labor.

Fig. 1 is a schematic diagram of the overall structure of a precooler for an aero-engine according to an embodiment of the present application;

Fig. 2 is a partial structural schematic diagram of a precooler for an aero-engine according to another embodiment of the present application;

Fig. 3 is a schematic structural diagram of a heat exchange assembly according to yet another embodiment of the present application.

Explanation of reference signs:

1. Header component; 2. Heat exchange component; 3. Micro tube; 4. Hollow cavity; 41. First cavity; 42. Second cavity; 5. Diverter tube; 51. Diverter hole; 6. Flow tube; 61, collecting hole; 7, liquid inlet; 8, liquid outlet; 9, partition; 91, ventilation hole; 10, through hole; 11, the first mounting plate; 12, the second mounting plate ; 13, U-shaped splitter plate; 14, mounting holes.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present application with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of them. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of this application.

In the related art, the heat exchange tubes used in conventional size tube bundle heat exchangers have limited heat exchange capacity, which makes it difficult to meet the strong pre-cooling requirements under high Mach number conditions. The micro-tube 3-bundle precooler has high compactness and heat exchange capacity, and can complete efficient heat exchange with incoming high-temperature air in a very short time. Therefore, the microtube 3-bundle precooler is the main precooler used in aerospace vehicles to ensure the normal operation of aero-engines. For the problems existing in the background technology, it can be seen that although the microtube 3-bundle precooler in the prior art meets the requirements of the engine precooler for compactness and heat exchange capacity, new problems arise, such as: There are many problems such as thermal stress caused by uneven temperature distribution in the quenching process, vibration caused by air sweeping across the heat transfer tube, large welding assembly of the three bundles of microtubes, and high maintenance costs.

At present, in order to solve some of the problems existing in the precooler with 3 bundles of microtubes in the market, some researchers have proposed a radially offset precooler, through which multiple heat exchange components 2 are coaxially connected step by step, reducing the temperature to a certain extent. However, in the actual manufacturing and assembly process, it is necessary to ensure a highly consistent concentricity between the microtubes 3 in the heat exchange assembly 2 of each layer, and the step-by-step welding of the radial stacked structure will increase the assembly Difficulty, the project is more difficult to realize, so the effect of improvement is not obvious. In addition, there is no relevant solution to the other problems of the microtube 3-bundle precooler, and the further development of the aero-engine precooler is still in a blank stage.

In view of this, the embodiment of the present application provides a pre-cooler for aero-engines, which is assembled into a modular pre-cooler body by using heat exchange components 2 in a limited space, and is easy to manufacture, assemble and disassemble by using modularization 3 bundles of straight-tube microtubes with a short length can be installed on the modular heat exchange assembly 2, providing an aero-engine precooler with a combination of high compactness and strong heat exchange capacity, and both manufacturing The design scheme integrates the advantages of low assembly difficulty, low maintenance cost, and resistance to flow-induced vibration.

Referring to Figures 1-2, Figure 1 is a schematic diagram of the overall structure of a precooler for an aero-engine shown in the present invention; Figure 2 is a schematic diagram of a partial structure of a pre-cooler for an aero-engine shown in the present invention. Design scheme of the present invention is as follows:

A precooler for an aero-engine, comprising two annular header parts 1 and a plurality of heat exchange assemblies 2, each heat exchange assembly 2 comprising a first mounting plate 11 and a second mounting plate 12;

Both the first mounting plate 11 and the second mounting plate 12 are provided with a hollow cavity 4, and a plurality of microtubes 3 are connected between the first mounting plate 11 and the second mounting plate 12, and the two ends of each microtube 3 are respectively It communicates with the hollow cavity 4 on the first mounting plate 11 and the second mounting plate 12; among them, a plurality of microtubes 3 form a gap for air to circulate from the outside to the inside;

Wherein, a plurality of heat exchange components 2 are assembled between two header parts 1, and the first mounting plate 11 and the second mounting plate 12 of each assembled heat exchange component 2 intersect the two header parts 1;

Wherein, each header part 1 is provided with a plurality of working medium flow holes communicating with the hollow cavity 4 of each heat exchange assembly 2, and the cooling working medium flows into the hollow cavity 4 through the working medium flow holes, and passes through the hollow cavity. The body 4 flows into the microtube 3 to cool the air circulating in the gap.

Specifically, by assembling a plurality of heat exchange components 2 between two annular header parts 1, the plurality of heat exchange components 2 abut against each other to form a sleeve-shaped heat exchanger with the heat exchange components 2 as the wall surface of the circular tube. thermal structure. As shown in Figure 1, the white arrow is the direction of air flow, the air flows from the outer wall of the tube to the inner wall of the tube, the cooled air flows out from the annular opening, and finally enters the aero-engine. Wherein, the assembly of the precooler and the engine is the same as that of the existing precooler, and the present invention does not repeat them in detail. Each heat exchange assembly 2 has two mounting plates and two hollow cavities 4. Taking a single heat exchange assembly 2 as an example, the first mounting plate 11 and the first cavity 41 are integrally formed, and the second mounting plate 12 and The second cavity 42 is integrally formed, and the microtube 3 communicates the first cavity 41 and the second cavity 42, so that the cooling medium flows from the first cavity 41 through the microtube 3 to the second cavity 42, or Flow from the second cavity 42 through the microtube 3 to the first cavity 41, or flow from the first cavity 41 and the second cavity 42 to the opposite second cavity 42 and the second cavity 42 after passing through the microtube 3 A cavity 41 .

As shown in FIG. 1 , the two header parts 1 are a front header part and a rear header part from front to back, and the annular opening of the front header part communicates with the engine. The intersection of the first mounting plate 11 and the two header parts 1 is that the two ends of the first mounting plate 11 are welded on the front header part and the rear header part, and the intersection of the second mounting plate 12 and the two header parts 1 is the second The two ends of the two mounting plates 12 are welded on the front header part and the rear header part. Specifically, the first mounting plate 11 and the second mounting plate 12 are perpendicular to the radial direction of the header part 1, and the plurality of microtubes 3 between the first mounting plate 11 and the second mounting plate 12 are connected to the radial direction of the header part 1. The peripheral direction is close to parallel to form a number of annular microtube layers stacked along the radial direction of the header part 1. The microtubes 3 are more compact, and the contact area between the microtubes 3 and air is increased, and the overall heat exchange capacity is significantly improved. .

Wherein, the first mounting plate 11 and the second mounting plate 12 are mirror images, and the microtubes 3 are vertically connected to the two opposite mounting plates to form a rectangular heat dissipation assembly. Taking the first mounting plate 11 as an example, the first mounting plate 11 is a rectangular plate-shaped structure, the length of which is the same as the distance between the two header parts 1, so that the first mounting plate 11 is fixed on the two header parts 1; The height is the same as the distance between the outer ring and the inner ring of the header part 1, so that in a limited installation space, the first installation plate 11 has the optimal compactness of the microtubes 3 on the plate surface formed by the length and height. The first mounting plate 11 is provided with a plurality of mounting holes 14 through which the microtube 3 is welded on the first mounting plate 11 and communicated with the first cavity 41 . The first cavity 41 is a rectangular cavity, welded to the first mounting plate 11, the first cavity 41 is provided with a through hole 10, and the through hole 10 communicates with the working medium flow hole on the header part 1, so as to The cooling working fluid in the header part 1 flows into the multiple first cavities 41 respectively through the multiple working fluid flow holes.

In this embodiment, since a plurality of heat exchange components 2 are modularly assembled to form the main body of the precooler, the distance between the first mounting plate 11 and the second mounting plate 12 is equal to the length of the microtube 3, so that the required The length of the microtube 3 is short, which solves the problem of flow-induced vibration caused by the excessive length of the microtube 3 in the traditional structure; because the length of the microtube 3 is relatively short, the microtube 3 is linearly welded on the two mounting plates along the tube length direction, The installation accuracy is higher; multiple installation holes 14 can be set along the length direction and height direction of the mounting plate, thereby forming a microtube layer along the length direction, and forming several microtube layers along the height direction, and the compactness between the microtube layers Compared with the traditional microtube 3-bundle precooler, it is higher, and does not need to maintain the concentricity between each layer, and the difficulty of welding is greatly reduced; multiple heat exchange components 2 flow into the cooling medium at the same time, so that the precooler The overall flow distribution is more even. The invention realizes the modular assembly of the heat exchange component 2 with strong heat exchange capacity, high reliability and low engineering realization difficulty into the main body of the precooler, and provides a precooler with good heat exchange performance, strong anti-vibration ability, Design scheme with low maintenance cost and low manufacturing and assembly difficulty.

In a specific implementation, there is a branch pipe 5 on one header part 1, and a header 6 is arranged on the other header part 1;

The distribution pipe 5 is provided with a plurality of distribution holes 51 communicating with the hollow cavity 4 on the first mounting plate 11;

The manifold 6 is provided with a plurality of manifold holes 61 communicating with the hollow cavity 4 on the second mounting plate 12;

Wherein, the cooling working fluid flows into the hollow cavity 4 on the first mounting plate 11 from a plurality of distribution holes 51, flows into the microtube 3 through the corresponding hollow cavity 4, and flows from the microtube 3 to the second mounting plate. The hollow cavity 4 on the plate 12 flows out of the hollow cavity 4 through a plurality of collecting holes 61 .

Specifically, a margin of several millimeters is left at the inlet and outlet of the heat exchange assembly 2 for welding with the header part 1 through the diversion holes 51 and the manifold holes 61; the manifold 6 and the manifold 5 need to be welded Corresponding distribution holes 51 and collecting holes 61 are covered to form a complete cooling medium flow path. In the cooling medium flow path, a liquid inlet 7 is provided on the front end surface of the branch pipe 5 of the front header part 1, for passing the cooling working medium into the branch pipe 5, and the rear end surface of the branch pipe 5 is provided with a A plurality of diversion holes 51 communicated with the first cavity 41 divide the cooling medium and flow to the plurality of first cavities 41, and are opened on the front end surface of the header 6 of the rear header part 1 to communicate with the second cavity 42 There are a plurality of collecting holes 61, and the rear end surface is provided with a liquid outlet 8, which is used to flow the heat-exchanged cooling working fluid out of the second cavity 42, so that the cooling working fluid passes through the first cavity from the front header part 1 in sequence The body 41 , the micropipe 3 and the second cavity 42 flow out from the rear header part 1 .

In a feasible specific embodiment, the branch pipe 5 and the collecting pipe 6 are respectively arranged on the inner ring edge or the outer ring edge of the corresponding header part 1 . In this embodiment, the cooling working fluid has multiple flow paths. When the manifold 5 is located on the inner ring edge of the front header part 1, and the collector tube 6 shell is located on the inner ring edge of the rear header part 1, the through hole 10 of the first cavity 41 and the second cavity The through hole 10 of 42 is located on the bottom diagonal line of the rectangular heat dissipation assembly; when the manifold 5 is located on the inner ring edge of the front header part 1, the collector tube 6 shell is located on the outer ring edge of the rear header part 1 At this time, the through hole 10 of the first cavity 41 and the through hole 10 of the second cavity 42 are located on the spatial diagonal of the rectangular heat dissipation assembly; When the collector 6 shell is located on the outer ring edge of the rear header part 1, the through hole 10 of the first cavity 41 and the through hole 10 of the second cavity 42 are located on the top surface of the rectangular cooling assembly. Angular line; when the manifold 5 is located on the outer ring edge of the front header part 1, and the collector tube 6 shell is located on the inner ring edge of the rear header part 1, the through hole 10 of the first cavity 41 is now and the through hole 10 of the second cavity 42 are located on the spatial diagonal of the rectangular heat sink assembly.

Wherein, the through-holes 10 of the first cavity 41 correspond to the distribution holes 51 one-to-one, and the through-holes 10 of the second cavity 42 correspond to the flow-collecting holes 61 one-to-one. Of course, the positions of the manifold 5 of the front header part 1 and the manifold 6 of the rear header part 1 can be exchanged, so that the cooling medium flows from the first cavity 41 through the microtube 3 to the second cavity 42 , or flow from the second cavity 42 to the first cavity 41 after passing through the microtube 3 . In this way, the method of modular construction and modular assembly in the embodiment of the present invention makes the low-temperature working medium flow distribution of the precooler to the internal heat exchange component 2 more uniform, and at the same time, the flow path of the cooling working medium can be selected in many forms, which can be Realize the regulation and control of the flow distribution of working fluid in local locations, thereby improving the uniformity of the overall heat transfer. Compared with the existing precooler, it has more advantages in heat exchange, anti-vibration and construction and assembly.

In the related art, the precooler at a high Mach number needs to drop the high-temperature air by at least 1000° C. within a response time of tens of milliseconds. During the quenching process, the temperature uniformity among the three bundles of microtubes is poor, resulting in a large temperature gradient between the three bundles of microtubes along the air flow direction, and the adjustment of the flight state causes the thermal stress caused by the temperature gradient change in the precooler Changes, resulting in thermal fatigue damage to metal materials, there are potential risks such as welding cracking of micro heat transfer tubes, and even affect the navigation safety of aerospace vehicles. As shown in FIG. 3 , FIG. 3 is a schematic structural diagram of the heat exchange assembly. The application proposes a preferred technical solution:

Both header components 1 are provided with a shunt 5 and a header 6;

A manifold component 1 is provided with a first manifold and a first manifold, and the first manifold is provided with a plurality of manifold holes 51 communicating with the hollow cavity 4 on the first mounting plate 11 and the first manifold A plurality of collecting holes 61 communicating with the hollow cavity 4 on the first mounting plate 11 are provided;

Another header component 1 is provided with a second manifold and a second manifold; the second manifold is provided with a plurality of manifold holes 51 communicating with the hollow cavity 4 on the second mounting plate 12 and a second manifold The pipe is provided with a plurality of collecting holes 61 communicating with the hollow cavity 4 on the second mounting plate 12;

Each hollow cavity 4 is divided into a plurality of first regions and a plurality of second regions; wherein,

The first branch pipe, the second header pipe and the corresponding microtubes 3 in the first area form the first cooling channel;

The second branch pipe, the first header pipe and the corresponding microtubes 3 in the second area form a second cooling channel;

The flow directions of the cooling working fluid in the first cooling channel and the second cooling channel are opposite.

Specifically, by distributing the manifold 5 and the manifold 6 on the front header part 1 and the rear header part 1, the cooling medium flows from the split holes 51 of the two header parts 1 to the first one at the same time. After the cavity 41 and the second cavity 42 , the microtube 3 flows to the staggered flow path of the opposite second cavity 42 and the first cavity 41 . Under the staggered flow path, it is divided into the first cooling channel and the second cooling channel that are independent and have opposite flow directions, so that the adjacent heat exchange components inside the heat exchange assembly 2 can be realized without reducing the heat exchange capacity of the precooler. The countercurrent heat transfer in the tubes between the hot zones improves the uniformity of heat transfer inside a single module and alleviates the problems of welding cracking of micro heat transfer tubes caused by thermal stress.

In this embodiment, the hollow cavity 4 is provided with a plurality of U-shaped splitter plates 13, and the plurality of U-shaped splitter plates 13 are arranged alternately between the two sides of the hollow cavity 4, so that the fine particles in the hollow cavity 4 The tubes 3 are divided into microcapillaries 3 in the first region and microcapillaries 3 in the second region. The first cavity 41 opens two through-holes 10 near the front view surface of the front header part 1, respectively communicating with the diversion hole 51 of the first manifold of the front header part 1 and the manifold hole 61 of the first manifold. Communication; the second cavity 42 opens two through holes 10 near the rear view surface of the rear header part 1, respectively communicating with the split hole 51 of the second manifold of the rear header part 1 and the flow collector of the second manifold The hole 61 communicates.

In the first cooling channel, the cooling medium flows from front to back, and flows into the microtubes 3 in the first area in the first cavity 41, because the U-shaped splitter plate 13 in the first cavity 41 blocks the cooling The working fluid flows into the micropipe 3 in the second region of the first cavity 41 , so the cooling working fluid flows from the first region to the second cavity 42 and flows through the rear header part 1 . At the same time, in the second cooling passage, the cooling working fluid flows from back to front, and flows into the microtube 3 in the second area in the second cavity 42, because the U-shaped splitter plate in the second cavity 42 13 blocks the flow of the cooling medium into the micropipe 3 in the first area of the second cavity 42, so the cooling medium flows from part of the second area into the first cavity 41 and flows through the front header part 1 .

Wherein the distribution hole 51 of the first distribution pipe and the distribution hole 51 of the second distribution pipe must communicate with the first cavity 41 and the second cavity 42 respectively, so as to realize that the cooling working fluid passes into the first cavity 41 and the second cavity simultaneously. Interleaved flow is realized in cavity 42 . In this way, the cooling working medium forms a plurality of adjacent first and second regions in the rectangular heat exchange assembly 2, and the reverse flow of the working medium in the tube is realized between the adjacent heat exchange areas inside the assembly, improving the The uniformity of heat transfer makes the precooler work in a relatively uniform temperature field as a whole, reduces the influence of the internal thermal stress of the precooler caused by intense heat transfer, and reduces the welding cracking of the micro heat transfer tubes caused by thermal stress, etc. risk, improve the service life and safety of equipment;

It should be explained that the opening of the U-shaped splitter plate 13 faces the side where the splitter pipe 5 communicates with the through hole 10 of the first cavity 41 to form a first area, and the opening of the U-shaped splitter faces the header 6 and the first cavity. The second region formed on one side where the through hole 10 of the body 41 communicates.

In another feasible embodiment, both the first manifold and the second manifold are arranged on the inner ring edge of the corresponding header part 1, and the first manifold and the second manifold are both arranged on the corresponding on the outer ring edge of header member 1; or,

The first branch pipe and the second collecting pipe are arranged on the inner ring edge of the corresponding header part 1 , and the second branch pipe and the first collecting pipe are arranged on the outer ring edge of the corresponding header part 1 .

Specifically, the embodiments of the present invention can change the positions of the branch pipes 5 and the header pipes 6 to realize various forms of staggered flow paths. Exemplarily, when the first manifold is located at the inner edge of the front header part 1, the first manifold is located at the outer edge of the front header part 1, and the second manifold is located at the edge of the rear header part 1. The inner ring edge, the second distribution pipe is located at the outer ring edge of the rear header part 1. In this embodiment, the cooling medium flows from front to back: from the inner side flow hole 51 of the front header part 1 to the first Cavity 41, after the shunting in the first cavity 41, flows through the microtube 3 to the inner collecting hole 61 of the rear header part 1; 51 flows to the second cavity 42 , and flows through the microtube 3 to the outer collecting hole 61 of the front header part 1 after being divided in the second cavity 42 .

When the distribution holes 51 are respectively located at the inner and outer rings of the front header part 1 and the rear header part 1, the U-shaped splitter plate 13 in the first cavity 41 and the second cavity 42 should be relatively rectangular heat exchange The midline of component 2 is a mirror image.

Exemplarily, when the first manifold is located at the inner edge of the front header part 1, the first manifold is located at the outer edge of the front header part 1, and the second manifold is located at the edge of the rear header part 1. edge of the outer ring, the second branch pipe is located at the inner ring edge of the rear header part 1. In this embodiment, the flow of the cooling medium from front to back is as follows: from the inner side flow hole 51 of the front header part 1 to the first Cavity 41, after the shunt in the first cavity 41, flows through the microtube 3 to the outer collecting hole 61 of the rear header part 1; 51 flows to the second cavity 42 , and flows through the microtube 3 to the outer collecting hole 61 of the front header part 1 after being divided in the second cavity 42 .

When the distribution holes 51 are respectively located at the inner rings of the front header part 1 and the rear header part 1, the U-shaped splitter plate 13 in the first cavity 41 and the second cavity 42 should be relative to the rectangular heat exchange assembly 2. The midline is polar symmetric.

It can be understood that the first manifold can be located on the outer edge of the front header part 1, the first manifold can be located on the inner edge of the front header part 1, and the second manifold and the second collector can be arranged correspondingly. The location can realize the countercurrent heat exchange in the microtubes 3 in the adjacent first area and the second area inside the heat exchange assembly 2, the principle is the same as the above two examples, and this embodiment will not be described in detail.

As shown in Figures 1-3, it shows that when the first manifold is located at the inner edge of the front header part 1, and the first manifold is located at the outer edge of the front header part 1, the second manifold is located at the The outer ring edge of the rear header part 1, the second splitter is located in the precooler of the inner ring edge of the rear header part 1.

In another feasible example, the cross-sections of the manifold 5 and the collector 6 are segmented. The circular segment is a circular segment with a bottom plane formed by cutting a part of a circular pipe through a straight line. When the shunt tube 5 and the header tube 6 are welded on the inner ring edge and the outer ring edge of the ring-shaped part, the bottom plane is in contact with the ring-shaped part, and when the cooling medium continues to flow into the tube in large quantities, it has a stronger pressure bearing ability.

In yet another example, at least one partition 9 is connected between the first mounting plate 11 and the second mounting plate 12 , and the partition 9 is located between the plurality of microtubes 3 at intervals. The partition plate 9 has a supporting function and can increase the rigidity of a single heat exchange assembly 2, thereby improving the rigidity of the entire precooler. Further, a plurality of ventilation holes 91 are scattered on the partition plate 9 . Ventilation holes 91 are opened on the partition 9, and the air at different temperatures on both sides of the partition 9 can reach the other side through the ventilation holes 91, which plays the role of mixed flow, reduces the temperature difference of the air on both sides of the partition 9, and further improves the temperature outside the tube. The uniformity of heat exchange in the air.

The flow and heat transfer process will be described below in conjunction with Figures 1-3. The black arrows represent the flow direction of the cooling medium. After the liquid inlet 7 enters the second distribution pipe, it flows into the first distribution cavity and the second distribution cavity of each heat exchange component 2 after being divided through the distribution hole 51, and then the cooling liquid passes through the heat exchange component 2 The U-shaped splitter plate 13 performs a secondary split, the coolant flows through the first cavity 41 from front to back, flows through the microtubes 3 in the first area to the second cavity 42, and at the same time the coolant passes through the second cavity from back to front Body 42 flows through the microtubes 3 in the second area to flow to the first cavity 41, because the microtubes 3 in the adjacent first area and the second area are divided by the shunt chambers on different sides, thus forming a phase The countercurrent flow of the working medium in the tube between the adjacent heat exchange areas. During the above process, the cooling liquid in the microtube 3 and the high-temperature air outside the tube fully exchange heat. At the same time, the ventilation holes 91 on the partition 9 are conducive to realizing The mixed flow of air on both sides of the partition 9 makes the heat exchange on the air side more uniform; since the precooler is installed in the middle and rear section of the air intake, the annular opening of the rear header part 1 in Fig. 1 has been replaced by other air intake parts Blocking, so the high-temperature air outside the tube will flow out of the precooler from the annular opening of the front header part 1 after precooling; the cooling liquid in the tube will continue to flow along the microtube 3 to the hollow cavity 4 on the other side after heat exchange , complete the primary confluence in the hollow cavity 4, then flow out from the collecting hole 61, complete the secondary confluence in the collecting pipe 6, and finally flow out of the cooling liquid passage from the liquid outlet 8, completing the process of cooling high-temperature air.

It should be noted that each embodiment in this specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. For the same and similar parts in each embodiment, refer to each other, that is, Can.

It should also be noted that, in this article, the orientations or positional relationships indicated by the terms "upper", "lower", "left", "right", "inner", "outer" etc. are based on the orientation or positional relationship shown in the drawings. The positional relationship is only for the convenience of describing the present invention and simplifying the description, but does not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another and do not necessarily require or imply any such relationship between the entities or operations. no actual relationship or order, nor should it be construed as indicating or implying relative importance. Furthermore, the term "comprising" or any other variation thereof is intended to cover a non-exclusive inclusion such that a process, method, article, or terminal device comprising a set of elements includes not only those elements but also other elements not expressly listed , or also include elements inherent in such a process, method, article, or terminal equipment.

A precooler for aero-engines provided by this application has been introduced in detail above. In this paper, specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the above examples are only used to help understanding This application and the contents of this specification should not be construed as limiting the application. At the same time, for those of ordinary skill in the art, according to the present application, there will be changes in different forms in the specific implementation methods and application ranges, and it is not necessary and impossible to exhaustively list all the implementation methods here. Obvious changes or modifications are still within the protection scope of the present application.

Claims (9)

1. A precooler for an aircraft engine, comprising two annular header members and a plurality of heat exchange assemblies, each heat exchange assembly comprising a first mounting plate and a second mounting plate;

the first mounting plate and the second mounting plate are both provided with hollow cavities, a plurality of micro-tubes are connected between the first mounting plate and the second mounting plate, and two ends of each micro-tube are respectively communicated with the hollow cavities on the first mounting plate and the second mounting plate; wherein gaps for air to flow from outside to inside are formed among the micro-tubes;

the first mounting plate and the second mounting plate being perpendicular to a radial direction of the header assembly, a plurality of the microtubes being arranged between the first mounting plate and the second mounting plate in a direction approximately parallel to a circumferential direction of the header assembly; the first mounting plate and the second mounting plate are in mirror symmetry, and the microtubes are vertically connected to the two opposite mounting plates to form a rectangular heat dissipation assembly;

the heat exchange assemblies are assembled between the two header parts, the heat exchange assemblies are abutted against each other to form a sleeve-shaped heat exchange structure taking the heat exchange assemblies as circular tube wall surfaces, and the first mounting plate and the second mounting plate of each heat exchange assembly after assembly are intersected with the two header parts;

and each header part is provided with a plurality of working medium flowing holes communicated with the hollow cavity of each heat exchange assembly, and cooling working medium flows into the hollow cavity through the working medium flowing holes and flows into the microtubes through the hollow cavity so as to cool air circulating in the gaps.

2. A precooler for an aircraft engine as claimed in claim 1, wherein one of the header members is provided with a flow dividing tube and the other header member is provided with a flow collecting tube;

a plurality of shunt holes communicated with the hollow cavity on the first mounting plate are formed in the shunt pipe;

the collecting pipe is provided with a plurality of collecting holes communicated with the hollow cavity on the second mounting plate;

the cooling working medium flows into the hollow cavity on the first mounting plate from the plurality of flow distribution holes, flows into the micro-tubes through the corresponding hollow cavities, flows into the hollow cavity on the second mounting plate from the micro-tubes, and flows out of the hollow cavity through the plurality of flow collecting holes.

3. A precooler for an aircraft engine as claimed in claim 2,

the shunt tubes and the collecting tubes are respectively arranged on the inner ring edge or the outer ring edge of the corresponding collecting pipe component.

4. A precooler for an aircraft engine as claimed in claim 1, wherein both header members are provided with flow dividing tubes and flow collecting tubes;

a first shunt pipe and a first collecting pipe are arranged on one collecting pipe part, the first shunt pipe is provided with a plurality of shunt holes communicated with the hollow cavity on the first mounting plate, and the first collecting pipe is provided with a plurality of collecting holes communicated with the hollow cavity on the first mounting plate;

a second shunt pipe and a second shunt pipe are arranged on the other header part; the second flow dividing pipe is provided with a plurality of flow dividing holes communicated with the hollow cavity on the second mounting plate, and the second flow collecting pipe is provided with a plurality of flow collecting holes communicated with the hollow cavity on the second mounting plate;

each hollow cavity is divided into a plurality of first areas and a plurality of second areas; wherein,

the first flow dividing pipe, the second flow dividing pipe and the corresponding micro-fine pipes in the first area form a first cooling channel;

the second flow dividing pipe, the first flow collecting pipe and the corresponding micro-fine pipe in the second area form a second cooling channel;

the flow directions of the cooling working mediums in the first cooling channel and the second cooling channel are opposite.

5. A precooler for an aircraft engine as claimed in claim 4,

the first flow dividing pipe and the second flow dividing pipe are arranged on the inner ring edge of the corresponding header part, and the first flow dividing pipe and the second flow dividing pipe are arranged on the outer ring edge of the corresponding header part; or,

the first flow dividing pipe and the second flow dividing pipe are arranged on the corresponding inner ring edge of the header part, and the second flow dividing pipe and the first flow dividing pipe are arranged on the corresponding outer ring edge of the header part.

6. The precooler for an aircraft engine according to claim 4, wherein a plurality of U-shaped flow distribution plates are arranged in the hollow cavity, and the plurality of U-shaped flow distribution plates are arranged in a staggered manner between two sides of the hollow cavity to divide the microtubes in the hollow cavity into microtubes in a first area and microtubes in a second area.

7. A precooler for an aircraft engine as claimed in claim 2 or claim 4, wherein the cross-sections of the flow-dividing tube and the flow-collecting tube are scalloped.

8. The precooler for an aircraft engine of claim 1, wherein at least one baffle is coupled between the first mounting plate and the second mounting plate, the baffle being spaced between the plurality of microtubes.

9. A precooler for an aircraft engine as claimed in claim 8, wherein a plurality of ventilation holes are dispersed in the baffle.

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