Integrated Structure of Inlet Air Precooling Heat Exchanger and Splitter Plate and Aeroengine

Abstract

The present disclosure relates to the technical field of pre-cooling heat exchangers for high-speed engines, and in particular, provides an integrated structure of an intake pre-cooling heat exchanger and a splitter plate, and an aero-engine. The integrated structure of the intake pre-cooling heat exchanger and the splitter plate includes a pre-cooling heat exchanger, a splitter plate, and a connecting member; the pre-cooling heat exchanger and the splitter plate are used to be installed in the intake duct; a partition member is formed in the intake duct, and the partition member divides the intake duct into a ram air passage and a turbine passage; both the pre-cooling heat exchanger and the splitter plate are rotatably connected to the connecting member; the connecting member is installed on the partition member; the pre-cooling heat exchanger and the splitter plate have at least three working states: in the first working state, the pre-cooling heat exchanger and the splitter plate block the ram air passage; in the second working state, the pre-cooling heat exchanger blocks the turbine passage, and the splitter plate blocks the ram air passage; in the third working state, the pre-cooling heat exchanger and the splitter plate block the turbine passage. The occupied axial length is shortened, which is convenient for the structural arrangement of the pre-cooling heat exchanger in the flow passage.

Description

Technical Field

[0001] The present disclosure relates to the technical field of high-speed engine pre-cooling heat exchangers, and particularly to an integrated structure of an intake pre-cooling heat exchanger and a splitter plate and an aeroengine. Background Art

[0002] The high-speedization of aircraft has extremely important military and civilian values. The combination of an aero-turbine engine and a ramjet to form a turbojet-boundary layer diffusion controlled combustion ramjet combined cycle engine (TBCC) is the mainstream solution. However, there is a gap between the maximum speed of the aero-turbine engine that can meet the aircraft thrust requirement and the minimum speed of the ramjet, commonly known as the thrust gap, which severely restricts the development of TBCC technology.

[0003] The aero-turbine engine has the characteristics of vertical takeoff and landing, reusability, and high specific impulse, and is the mainstream aeroengine solution. However, the aerodynamic heating effect usually limits the flight limit of modern advanced aero-turbine engines to Ma2.5. One of the main solutions to further increase the flight speed of the turbine is to use a heat exchanger structure to cool the intake air. The temperature of the air flow at the turbine inlet is reduced, offsetting the increase in the intake air temperature caused by the aerodynamic heating effect during high-speed flight, enabling the turbine to fly at a higher speed, and thus enabling a relay with the ramjet.

[0004] The following problems still exist in the prior art. The pre-cooling heat exchanger often occupies a relatively long axial length in the flow channel in front of the engine. For example, in the patent document CN115571350B, it brings difficulties to the structural arrangement of the pre-cooling heat exchanger in the flow channel. Summary of the Invention

[0005] In view of the above problems, the present disclosure is proposed. The present disclosure provides an integrated structure of an intake pre-cooling heat exchanger and a splitter plate and an aeroengine.

[0006] According to one aspect of the present disclosure, an integrated structure of an intake pre-cooling heat exchanger and a splitter plate is provided, which includes a pre-cooling heat exchanger, a splitter plate, and a connecting member;

[0007] The pre-cooling heat exchanger and the splitter plate are used to be installed in the intake duct; a partition is formed in the intake duct, and the partition divides the intake duct into a ramjet channel and a turbine channel;

[0008] Both the pre-cooling heat exchanger and the splitter plate are rotatably connected to the connecting member; the connecting member is installed on the partition; ventilation holes are formed on the pre-cooling heat exchanger;

[0009] The pre-cooling heat exchanger and the flow dividing plate have at least three working states:

[0010] In the first working state, the pre-cooling heat exchanger and the flow dividing plate block the stamping channel;

[0011] In the second working state, the pre-cooling heat exchanger blocks the turbine channel, and the flow dividing plate blocks the stamping channel;

[0012] In the third working state, the pre-cooling heat exchanger and the flow dividing plate block the turbine channel.

[0013] For the integrated structure of the intake air pre-cooling heat exchanger and the flow dividing plate according to one aspect of the present disclosure, the connecting member includes a connecting frame, a first rotating shaft, a second rotating shaft, and a third rotating shaft;

[0014] The connecting frame is fixedly arranged on the partition member, and the first rotating shaft, the second rotating shaft, and the third rotating shaft are all rotatably connected to the connecting frame;

[0015] The pre-cooling heat exchanger is fixedly connected to the first rotating shaft, and the flow dividing plate is fixedly connected to the second rotating shaft; the third rotating shaft is used for connecting with a driver; the third rotating shaft is used for separately driving the first rotating shaft and the second rotating shaft to rotate.

[0016] For the integrated structure of the intake air pre-cooling heat exchanger and the flow dividing plate according to one aspect of the present disclosure, a first gear is installed on the first rotating shaft, and a second gear is installed on the second rotating shaft;

[0017] The third rotating shaft is provided with a partial tooth structure along the circumferential direction;

[0018] The partial tooth structure can be intermittently drivingly connected to the first gear; the partial tooth structure can be intermittently drivingly connected to the second gear; so that when the third rotating shaft rotates in one direction, the pre-cooling heat exchanger and the flow dividing plate can be switched to the first working state, and when the third rotating shaft rotates in the other direction, the pre-cooling heat exchanger and the flow dividing plate can be switched to the third working state.

[0019] For the integrated structure of the intake air pre-cooling heat exchanger and the flow dividing plate according to one aspect of the present disclosure, during the process of the pre-cooling heat exchanger and the flow dividing plate switching from the first working state to the third working state, or from the third working state to the first working state, the second working state can be passed through.

[0020] For the integrated structure of the intake air pre-cooling heat exchanger and the flow dividing plate according to one aspect of the present disclosure, the pre-cooling heat exchanger and the flow dividing plate further have a transition state, and the transition state is: the pre-cooling heat exchanger does not completely block the turbine channel or the flow dividing plate does not completely block the stamping channel.

[0021] According to an aspect of the present disclosure, for the integrated structure of the intake pre-cooling heat exchanger and the splitter plate, when the speed is lower than the first speed, the pre-cooling heat exchanger and the splitter plate are in the first working state.

[0022] According to an aspect of the present disclosure, for the integrated structure of the intake pre-cooling heat exchanger and the splitter plate, when the speed is not less than the first speed and less than the second speed, the pre-cooling heat exchanger and the splitter plate are in the second working state.

[0023] According to an aspect of the present disclosure, for the integrated structure of the intake pre-cooling heat exchanger and the splitter plate, when the speed is not less than the second speed, the pre-cooling heat exchanger and the splitter plate are in the third working state.

[0024] For the integrated structure of the intake pre-cooling heat exchanger and the splitter plate according to an aspect of the present disclosure, the first speed is between 2.2 and 2.8 Mach, and the second speed is between 3.2 and 3.8 Mach.

[0025] According to another aspect of the present disclosure, an aeroengine is further provided, which includes the integrated structure of the intake pre-cooling heat exchanger and the splitter plate as described in any one of the above.

[0026] As will be described in detail below, for the integrated structure of the intake pre-cooling heat exchanger and the splitter plate and the aeroengine according to the embodiments of the present disclosure, by setting the pre-cooling heat exchanger and the splitter plate as an integrated structure rotatably arranged with a connecting member, it can be switched between the ram channel and the turbine channel. By rotating the pre-cooling heat exchanger and the splitter plate, the pre-cooling heat exchanger and the splitter plate can have at least three working states. While providing multiple working states, the occupied axial length is shortened, which is convenient for the structural arrangement of the pre-cooling heat exchanger in the flow channel.

[0027] It should be understood that both the foregoing general description and the following detailed description are exemplary and are intended to provide further explanation of the claimed technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] By describing the embodiments of the present disclosure in more detail in conjunction with the drawings, the above and other objects, features, and advantages of the present disclosure will become more apparent. The drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation to the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0029] Figure 1 is a schematic structural diagram of the integrated structure of the intake pre-cooling heat exchanger and the splitter plate proposed by the present disclosure in the first working state;

[0030] Figure 2 isFigure 1 Partial enlarged schematic view;

[0031] Figure 3 is a schematic structural view of the integrated structure of the intake pre-cooling heat exchanger and the flow splitter plate proposed by the present disclosure in the second working state;

[0032] Figure 4 is Figure 3 Partial enlarged schematic view;

[0033] Figure 5 is a schematic structural view of the integrated structure of the intake pre-cooling heat exchanger and the flow splitter plate proposed by the present disclosure in the third working state;

[0034] Figure 6 is Figure 5 Partial enlarged schematic view;

[0035] Figure 7 is a perspective view of the integrated structure of the intake pre-cooling heat exchanger and the flow splitter plate proposed by the present disclosure;

[0036] Figure 8 is Figure 7 Partial enlarged schematic view.

[0037] Explanation of reference numerals:

[0038] 1 - Pre-cooling heat exchanger, 2 - Flow splitter plate, 3 - Connecting piece, 4 - Intake passage;

[0039] 31 - Connecting frame, 32 - First rotating shaft, 33 - Second rotating shaft, 34 - Third rotating shaft, 35 - First gear; 36 - Second gear, 37 - Partial tooth structure;

[0040] 41 - Partition piece, 42 - Stamping passage, 43 - Turbine passage. Detailed implementation manners

[0041] In order to make the objectives, technical solutions and advantages of the present disclosure more obvious, exemplary embodiments according to the present disclosure will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure. It should be understood that the present disclosure is not limited by the exemplary embodiments described herein.

[0042] Regarding the problems raised in the background art, in the present disclosure, the heat exchanger and the flow splitter plate can be made into an integrated structure to solve. Through the combination of the thin-layer pre-cooling heat exchanger and the flow splitter plate, smooth switching among three main working states and transitional states is achieved, and the axial dimension occupied by the pre-cooling heat exchanger is saved.

[0043] Specifically, please refer to Figures 1 to 8, the present disclosure proposes an integrated structure of an intake pre-cooling heat exchanger and a splitter plate, which includes a pre-cooling heat exchanger 1, a splitter plate 2, and a connecting member 3; the connecting member 3 is used to connect the pre-cooling heat exchanger 1 and the splitter plate 2 and provide support.

[0044] Specifically, the pre-cooling heat exchanger 1 and the splitter plate 2 are used to be installed in the intake duct 4; a partition member 41 is formed in the intake duct 4, and the partition member 41 divides the intake duct 4 into a ram channel 42 and a turbine channel 43. In a specific implementation, the partition member 41 can be the wall of the turbine channel 43.

[0045] The pre-cooling heat exchanger 1 is used to cool the air entering the turbine channel 43. The splitter plate 2 is used to split the gas entering the ram channel 42 and the gas entering the turbine channel 43 to achieve the distribution of air.

[0046] Specifically, both the pre-cooling heat exchanger 1 and the splitter plate 2 are rotatably connected to the connecting member 3; the connecting member 3 is installed on the partition member 41; ventilation holes are formed in the pre-cooling heat exchanger 1; that is, air can pass through the pre-cooling heat exchanger 1 but cannot pass through the splitter plate.

[0047] The pre-cooling heat exchanger 1 and the splitter plate 2 have at least three working states:

[0048] Please refer to Figure 1 and Figure 2 , in the first working state, the pre-cooling heat exchanger 1 and the splitter plate 2 block the ram channel 42; when the speed is lower than the first speed, the pre-cooling heat exchanger 1 and the splitter plate 2 are in the first working state. That is, when the speed of the aircraft is lower than the first speed, it is in the low mode, and air enters through the turbine channel, and the turbine engine works while the ramjet engine does not work. In a specific implementation, the first speed is between 2.2 and 2.8 Mach, and preferably 2.5 Mach.

[0049] Please refer to Figure 3 and Figure 4 , in the second working state, the pre-cooling heat exchanger 1 blocks the turbine channel 43, and the splitter plate 2 blocks the ram channel 42. When the speed is not less than the first speed and less than the second speed, the pre-cooling heat exchanger 1 and the splitter plate 2 are in the second working state. At this time, it is in the medium-speed mode, and air enters through the turbine channel, passes through the pre-cooling heat exchanger 1 and enters the turbine engine, and the turbine engine works while the ramjet engine does not work. In a specific implementation, the second speed is between 3.2 and 3.8 Mach, and preferably 3.5 Mach.

[0050] Please refer to Figure 5 and Figure 6, in the third working state, the precooling heat exchanger 1 and the flow dividing plate 2 block the turbine passage 43. When the speed is not less than the second speed, the precooling heat exchanger 1 and the flow dividing plate 2 are in the third working state. At this time, in the high-speed mode, air enters from the ram air passage, the ramjet engine works, and the turbine engine does not work. Preferably, the precooling heat exchanger 1 can be a thin-layer precooler.

[0051] Through this arrangement method, the axial dimension can be saved, which is convenient for arranging on the aeroengine.

[0052] When adopting the integrated structure of the precooling heat exchanger and the flow dividing plate, another problem appears. According to the different engine speeds, the precooling heat exchanger and the flow dividing plate need to rotate to different positions, and they need to have the ability of bi-directional rotation. It is necessary to accurately judge and control their rotation positions. At the same time, to avoid the collision between the flow dividing plate and the precooling heat exchanger and damage the heat exchange structure, it is also necessary to accurately control their respective positions. Finally, the switching of the three modes is not achieved overnight, but a continuous and smooth process, that is, the engine mode conversion process, and it is also necessary to accurately control their respective positions.

[0053] The traditional cable-type device can produce a motion effect, but it is difficult to achieve bi-directional rotation and it is not easy to accurately control the rotation position. If a complex position feedback and control mechanism is adopted, the system complexity is too large.

[0054] For this reason, please refer to Figure 7 and Figure 8 , in the present disclosure, the connecting member 3 includes a connecting frame 31, a first rotating shaft 32, a second rotating shaft 33 and a third rotating shaft 34. Specifically, the connecting frame 31 is fixedly arranged on the partition member 41, and the first rotating shaft 32, the second rotating shaft 33 and the third rotating shaft 34 are all rotatably connected to the connecting frame 31; the precooling heat exchanger 1 is fixedly connected to the first rotating shaft 32, and the flow dividing plate 2 is fixedly connected to the second rotating shaft 33; the third rotating shaft 34 is used for connecting with a driver; the third rotating shaft 34 is used for separately driving the first rotating shaft 32 and the second rotating shaft 33 to rotate.

[0055] In specific implementation, a first gear 35 is installed on the first rotating shaft 32, and a second gear 36 is installed on the second rotating shaft 33. The third rotating shaft 34 is provided with partial tooth structures 37 along the circumferential direction; in specific implementation, the partial tooth structures 37 are multiple tooth structures distributed in a fan shape along the third rotating shaft 34. When the third rotating shaft 34 rotates in the same direction, the partial tooth structures 37 are respectively meshed with the first gear 35 and the second gear 36. That is, the partial tooth structures 37 are not meshed with the first gear 35 and the second gear 36 at the same time.

[0056] The partial tooth structure 37 can be intermittently and drivingly connected to the first gear 35; the partial tooth structure 37 can be intermittently and drivingly connected to the second gear 36; so that when the third rotating shaft 34 rotates in one direction, the precooling heat exchanger 1 and the flow dividing plate 2 can be switched to the first working state, and when the third rotating shaft 34 rotates in the other direction, the precooling heat exchanger 1 and the flow dividing plate 2 can be switched to the third working state.

[0057] During specific implementation, during the process of the precooling heat exchanger 1 and the flow dividing plate 2 being switched from the first working state to the third working state, or from the third working state to the first working state, the second working state can be passed through.

[0058] During specific implementation, taking the acceleration state of the aircraft as an example:

[0059] When the precooling heat exchanger 1 and the flow dividing plate 2 are in the first working state, the precooling heat exchanger 1 and the flow dividing plate 2 block the ram air passage 42. At this time, at the entrance of the ram air passage, along the entrance direction of the ram air passage, the precooling heat exchanger 1 and the flow dividing plate 2 are sequentially blocked. When acceleration is required, the third rotating shaft 34 is driven in the first direction. The partial tooth structure 37 on the third rotating shaft 34 first meshes with the first gear 35, and the precooling heat exchanger 1 is driven to the position where it blocks the turbine passage 43. During this process, the flow dividing plate 2 does not rotate and is switched from the first working state to the second working state. During the whole process, the ramjet engine does not work and the turbine engine works.

[0060] The third rotating shaft 34 is continuously driven to rotate in the first direction. The partial tooth structure 37 no longer meshes with the first gear 35, but begins to mesh with the second gear 36. As the third rotating shaft 34 continues to rotate, the second gear 36 starts to rotate until the flow dividing plate 2 is rotated to block the entrance of the turbine passage 43. At this time, it enters the third working state. Along the entrance direction of the turbine passage 43, the flow dividing plate 2 and the precooling heat exchanger 1 are sequentially covered.

[0061] During specific implementation, when the aircraft decelerates: the third rotating shaft 34 is rotated in the second direction, and the above process is sequentially switched from the third working state to the second working state until the first working state. During the specific implementation process, the partial tooth structure 37 first meshes with the second gear 36 and then meshes with the first gear 35. The first direction is the clockwise direction or the counterclockwise direction, and the second direction is opposite to the first direction.

[0062] During specific implementation, the precooling heat exchanger 1 and the flow dividing plate 2 further have a transition state, and the transition state is: the precooling heat exchanger 1 does not completely block the turbine passage 43 or the flow dividing plate 2 does not completely block the ram air passage 42.

[0063] There are two transition states. That is, during the process in which a part of the tooth structure 37 meshes with the first gear 35, the pre-cooling heat exchanger 1 partially blocks the turbine passage 43. The other is that during the process in which the partial tooth structure 37 meshes with the second gear 36, the diverter plate 2 partially blocks the ram passage.

[0064] According to another aspect of the present invention, an aero-engine is further provided, which includes the integrated structure of the intake pre-cooling heat exchanger and the diverter plate described in any one of the present disclosures.

[0065] As described above, with reference to the drawings, the integrated structure of the intake pre-cooling heat exchanger and the diverter plate and the aero-engine according to the embodiments of the present disclosure are described. The integrated structure of the intake pre-cooling heat exchanger and the diverter plate according to the embodiments of the present disclosure can be switched within the ram passage and the turbine passage by arranging the pre-cooling heat exchanger and the diverter plate into an integrated structure rotatably arranged with the connecting member. By rotating the pre-cooling heat exchanger and the diverter plate, the pre-cooling heat exchanger and the diverter plate can have at least three working states. While providing multiple working states, the occupied axial length is shortened, which is convenient for the structural arrangement of the pre-cooling heat exchanger in the flow passage.

[0066] The basic principles of the present disclosure have been described above in conjunction with specific embodiments. However, it should be noted that the advantages, advantages, effects, etc. mentioned in the present disclosure are only examples and not limitations. It cannot be considered that these advantages, advantages, effects, etc. are essential for each embodiment of the present disclosure. In addition, the above-mentioned specific details are only for the purpose of illustration and easy understanding, rather than limitations. The above details do not limit the present disclosure to necessarily adopt the above specific details to implement.

[0067] The block diagrams of the devices, apparatuses, equipment, and systems involved in the present disclosure are only illustrative examples and do not intend to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including", "comprising", "having", etc. are open-ended words, meaning "including but not limited to", and can be used interchangeably with each other. The words "or" and "and" used herein refer to the word "and / or", and can be used interchangeably with each other unless the context clearly indicates otherwise. The word "such as" used herein refers to the phrase "such as but not limited to", and can be used interchangeably with each other.

[0068] In addition, as used herein, the "or" used in the enumeration of items starting with "at least one" indicates a separate enumeration. For example, the enumeration of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (that is, A and B and C). In addition, the term "exemplary" does not mean that the described examples are preferred or better than other examples.

[0069] It should also be noted that in the systems and methods of the present disclosure, each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations should be regarded as equivalent solutions of the present disclosure.

[0070] Various changes, substitutions, and alterations to the technologies described herein can be made without departing from the teachings defined by the appended claims. In addition, the scope of the claims of the present disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of events, means, methods, and acts described above. Processes, machines, manufactures, compositions of events, means, methods, or acts that currently exist or will later be developed and that perform substantially the same function or achieve substantially the same result as the corresponding aspects described herein can be utilized. Accordingly, the appended claims include such processes, machines, manufactures, compositions of events, means, methods, or acts within their scope.

[0071] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to the broadest scope consistent with the principles and novel features disclosed herein.

[0072] The above description has been presented for purposes of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although several example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub - combinations thereof.

Claims

1. An integrated structure of an intake air precooling heat exchanger and a splitter plate, characterized in that, It includes a precooling heat exchanger (1), a flow dividing plate (2) and a connecting piece (3); The precooling heat exchanger (1) and the flow dividing plate (2) are used to be installed in the air inlet duct (4); a partition member (41) is formed in the air inlet duct (4), and the partition member (41) divides the air inlet duct (4) into a ram air passage (42) and a turbine passage (43); Both the precooling heat exchanger (1) and the flow dividing plate (2) are rotatably connected to the connecting piece (3); the connecting piece (3) is installed on the partition member (41); ventilation holes are formed on the precooling heat exchanger (1); The precooling heat exchanger (1) and the flow dividing plate (2) have at least three working states: In the first working state, the precooling heat exchanger (1) and the flow dividing plate (2) block the ram air passage (42); In the second working state, the precooling heat exchanger (1) blocks the turbine passage (43), and the flow dividing plate (2) blocks the ram air passage (42); In the third working state, the precooling heat exchanger (1) and the flow dividing plate (2) block the turbine passage (43).

2. The integrated structure of the intake air pre-cooling heat exchanger and the flow splitter plate according to claim 1, wherein The connecting piece (3) includes a connecting frame (31), a first rotating shaft (32), a second rotating shaft (33) and a third rotating shaft (34); The connecting frame (31) is fixedly arranged on the partition member (41), and the first rotating shaft (32), the second rotating shaft (33) and the third rotating shaft (34) are all rotatably connected to the connecting frame (31); The precooling heat exchanger (1) is fixedly connected to the first rotating shaft (32), and the flow dividing plate (2) is fixedly connected to the second rotating shaft (33); the third rotating shaft (34) is used to be connected to a driver; the third rotating shaft (34) is used to independently drive the first rotating shaft (32) and the second rotating shaft (33) to rotate.

3. The integrated structure of the intake air pre-cooling heat exchanger and the flow splitter according to claim 2, characterized in that, A first gear (35) is installed on the first rotating shaft (32), and a second gear (36) is installed on the second rotating shaft (33); Part of a tooth structure (37) is arranged on the third rotating shaft (34) along the circumferential direction; The part of the tooth structure (37) can be intermittently drivingly connected to the first gear (35); the part of the tooth structure (37) can be intermittently drivingly connected to the second gear (36); so that when the third rotating shaft (34) rotates in one direction, the precooling heat exchanger (1) and the flow dividing plate (2) can be switched to the first working state, and when the third rotating shaft (34) rotates in the other direction, the precooling heat exchanger (1) and the flow dividing plate (2) can be switched to the third working state.

4. The integrated structure of the intake air pre-cooling heat exchanger and the flow splitter plate according to claim 3, characterized in that, During the process of the precooling heat exchanger (1) and the flow dividing plate (2) being switched from the first working state to the third working state, or from the third working state to the first working state, they can pass through the second working state.

5. The integrated structure of the intake air precooling heat exchanger and the splitter plate according to any one of claims 1-4, characterized in that, The precooling heat exchanger (1) and the flow dividing plate (2) also have a transition state, and the transition state is: the precooling heat exchanger (1) does not completely block the turbine passage (43) or the flow dividing plate (2) does not completely block the ram air passage (42).

6. The integrated structure of the intake pre-cooling heat exchanger and the flow splitting plate according to any one of claims 1-4, characterized in that, When the speed is lower than the first speed, the precooling heat exchanger (1) and the flow dividing plate (2) are in the first working state.

7. The integrated structure of the intake air pre-cooling heat exchanger and the flow dividing plate according to claim 6, wherein When the speed is not less than the first speed and less than the second speed, the precooling heat exchanger (1) and the flow dividing plate (2) are in the second working state.

8. The integrated structure of the intake air pre-cooling heat exchanger and the flow splitting plate according to claim 6, characterized in that, When the speed is not less than the second speed, the precooling heat exchanger (1) and the flow dividing plate (2) are in the third working state.

9. The integrated structure of the intake air pre-cooling heat exchanger and the flow splitter plate according to claim 8, wherein The first speed is between 2.2 and 2.8 Mach, and the second speed is between 3.2 and 3.8 Mach.

10. An aero-engine, characterized in that, It includes the integrated structure of the intake air precooling heat exchanger and the flow dividing plate according to any one of claims 1-9.

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