A jet cooling device

Abstract

This application relates to an aircraft engine cooling system, and more particularly to a jet cooling device. Different flow gradient designs are employed in the nozzle design to ensure that, in a low state, when the incoming flow temperature is higher than the engine's allowable range but slightly overheated, some injection points are sprayed at a small state, ensuring the atomization effect of each injection point, thereby improving evaporation efficiency and ensuring the jet effect at a small state. When the inlet state is high and the inlet duct temperature is high, opening all nozzles at this time can also ensure atomization of each injection point, thereby ensuring effective evaporation, heat absorption, and cooling. This design ensures that the jet liquid is well atomized throughout the entire operating range. At the same time, under conditions of airflow distortion, its zoned and gradient flow design can effectively structure effective cooling and temperature distribution adjustments, effectively ensuring a good temperature field distribution at the outlet cross-section of the inlet duct jet section.

Description

Technical Field

[0001] The present application relates to an aircraft engine cooling system, and in particular to a jet cooling device. Background Art

[0002] During high Mach number flight, the engine's intake air temperature increases, and the unevenness of the intake airflow distribution also increases. This requires cooling the inlet air temperature before the engine inlet, ensuring uniform temperature distribution. Currently, direct injection points or evenly distributed liquid injection are commonly used to achieve localized cooling. However, when the engine inlet airflow is distorted, existing structures cannot adapt to the uneven flow distribution of the inlet gas flow across the same cross-section, and cannot achieve uniform temperature distribution at the outlet cross-section.

[0003] This patent proposes a cooling device with a stepped arrangement that can adapt to different intake conditions. Injection points with different performance distributions are set on the intake duct jet device, and cooling areas with different flow gradient arrangements are set, so that the jet area covers a wide flow and spray range. The spray full coverage method and distribution are adopted between the injection points to effectively improve and optimize the outlet temperature distribution of different intake distribution fields, and ensure the uniformity of the engine intake temperature.

[0004] The existing technical solutions and technologies are jet devices with multiple holes, which are arranged in a uniform distribution or hole distribution. The main disadvantages are as follows:

[0005] 1. It is impossible to ensure full coverage of the airflow cooling range, which may cause local high temperature and hot spots and fail to achieve the cooling effect.

[0006] 2. It is impossible to take into account the distorted air intake conditions and the injection point layout cannot be adjusted in a targeted manner during use;

[0007] 3. Its injection point cannot be set to different flow distribution areas, and the outlet temperature cannot be guaranteed to be uniform for locally distorted airflow. Summary of the Invention

[0008] In order to solve the above problems, the present application provides a jet cooling device, comprising:

[0009] An air intake device and a plurality of jet plates, the air intake device comprising an upper wall, a lower wall, and two side walls, each jet plate being mounted between the upper wall and the lower wall, and the plurality of jet plates being arranged at equal intervals on the same cross section of the air intake device;

[0010] Multiple vertical waterways are distributed on both sides of each jet plate, and multiple injection points are distributed at equal height intervals on each waterway. The same side of the jet plate is divided into multiple areas with gradually increasing areas from top to bottom, and nozzles with the same flow rate level are set at the injection points in each area;

[0011] When the air intake volume is within a first preset range, the water channel on the jet plate located at the front end of the airflow direction is opened; when the air intake volume is within a second preset range, every other water channel on the same side of the jet plate is opened; when the air intake volume is within a third preset range, all the water channels on the jet plate are opened.

[0012] Preferably, the first preset range is smaller than the second preset range, and the second preset range is smaller than the third preset range.

[0013] Preferably, the angle between the direction of the water mist sprayed from the spray point and the incoming air intake direction is 90 degrees, the water mist sprayed from the spray point forms an air cone structure, and the cone surface coverage angle is between 80-95 degrees.

[0014] Preferably, the conical water mist surfaces sprayed by two adjacent spraying points in the vertical direction intersect.

[0015] Preferably, the same side of the jet plate is divided into four areas from top to bottom, and the flow rate ratio of the nozzles in the four areas from top to bottom is 0.5:1:1.5:2.

[0016] Preferably, the ratio of the number of injection points in the four regions from top to bottom is 2:3:4:6.

[0017] Preferably, the water paths on both sides of the same jet plate (20) are arranged in a mirror image or staggered in the direction of airflow.

[0018] Preferably, the injection points on the same side of the jet plate are staggered in height direction.

[0019] Preferably, the distance between adjacent jet plates (20) is greater than the thickness of the jet plates (20).

[0020] Preferably, there is a certain distance between the uppermost nozzle of the jet plate (20) and the upper wall surface, and there is a certain distance between the lowermost nozzle and the lower wall surface, so that the water mist sprayed from the injection point will not be sprayed directly onto the wall surface.

[0021] The advantages of this application include: 1. Realizing a wide range of cooling area coverage by the jet; 2. Realizing excellent atomization and evaporation of the jet water under different intake flow conditions; 3. Realizing uniform temperature distribution at the outlet under uneven or distorted intake conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the installation position of the ejector in a preferred embodiment of the present application;

[0023] Figure 2 This is a schematic diagram of the mirror image arrangement of the ejector waterway in a preferred embodiment of the present application;

[0024] Figure 3 This is a schematic diagram of the staggered arrangement of the ejector waterway in a preferred embodiment of the present application;

[0025] Figure 4 This is a schematic diagram of the opening of the ejector water channel in a preferred embodiment of the present application when the air intake volume is in the second range;

[0026] Figure 5 This is a schematic diagram of the ejector waterway opening when the air intake volume is in the second range according to another preferred embodiment of the present application;

[0027] Figure 6 This is a schematic diagram of the injection point partitioning and parameter distribution on each side of the jet plate in another preferred embodiment of the present application;

[0028] Figure 7 Schematic diagram of the spray direction of the nozzle from a top view of another preferred embodiment of the present application;

[0029] Figure 8 This is a schematic diagram of the spray direction of the nozzle from the perspective of the airflow direction of another preferred embodiment of the present application. DETAILED DESCRIPTION

[0030] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0031] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0032] like Figure 1-Figure 7As shown in the schematic diagram, the present invention provides a stepped jet cooling device solution that can adapt to different intake conditions. The jet plate mainly includes a plurality of jet plates 20. The jet plates are installed on the middle section of the intake device 10 and are fixedly assembled from top to bottom. The jet plates are arranged at equal intervals on the same section, and the intervals are much larger than the thickness of the jet plates. Multiple rows of nozzles 30 are provided on both sides of the jet plates. The nozzles in the same row are connected by a branch pipe. A certain distance should be left between the uppermost nozzle and the lowermost nozzle in the same row and the intake shell.

[0033] The jet plates 20 arranged on the air intake section are distributed in a mirror-like manner side by side. The jet plates on both sides of the air intake cavity need to reserve a certain space below the air intake device cavity. The width of the space is about 3 times the radial width of the jet plate. Different injection areas are arranged on a single jet plate, and the space coverage of the injection area reaches 100%. The arrangement scheme is as follows: Figure 1-Figure 3 As shown, it can be used Figure 2 The row distribution in Figure 3 All jet plates mainly include two spray areas, positive and negative, with a total of 8 spray columns, 4 on each side, such as Figure 4-Figure 5 As shown, in the specific structural scheme, 2, 4, 6, and 8 are on the same side, and 1, 3, 5, and 7 are on the other side of the jet plate. There are a total of eight water columns, and each water column has 6-10 injection points. All injection points are distributed at equal height intervals on the jet plate and are at the same axial position along the airflow direction.

[0034] Jet nozzles of different area groups are set on the injection point on the same side of the jet plate, which is divided into 4 areas from top to bottom, such as Figure 6 As shown, each area is provided with different injection points. The first area is designed with 12 nozzles of the same flow level, the second area is set with 8 nozzles of the same flow level, the third area is set with 6 nozzles of the same flow level, and the fourth area is set with 4 nozzles of the same flow level.

[0035] The main parameters of the device described in the present invention are as follows:

[0036] The water jets on the back of the ejector are spaced apart with the same spacing, and the number of jet points on both sides is 1:1;

[0037] The front and back sides of the jet are divided into multiple spraying areas. The design can be adjusted according to the situation. The area should be 2-6 zones.

[0038] The ejector jet described in the present invention is divided into 4 regions, and the number of regional injection points and flow rate are both stepped. The main parameters include: the ratio of the number of injection points in the four regions (from bottom to top) is 6:4:3:2,

[0039] The flow numbers of the multiple injection point positions in each area of ​​each ejector plate of the ejector are consistent, but the four areas are different, and the ratio of the single point injection flow numbers in each of the four areas is 4:3:2:1;

[0040] The injection direction of the ejector's injection point is at an angle of 90 degrees to the incoming air intake direction. The injection point ejects air in a cone structure, and the cone coverage angle is between 80-95 degrees.

[0041] The working mode of the jet cooling device is as follows: the spray points of two adjacent jet plates have the same working mode, the water channels 101, 103, 105, 107 and 102, 104, 106, 108 on both sides of the jet plate spray crosswise, and the spray direction is perpendicular to the airflow direction, such as Figure 7 The water channels on the ejector have three operating modes. When the air intake is low, channels 2 and 3 (102, 103 injection) of all the ejector plates in the ejector device work. When the air intake increases to a certain level, channels 2, 3, 6, and 7 (102, 103, 106, and 107 injection) work simultaneously. When the air intake continues to increase, all eight water channels (101-108 injection) work simultaneously. When the aerospace plane is in a high Mach number flight state, its inlet airflow distribution may be distorted, resulting in a higher intake pressure below the incoming air and uneven velocity distribution along the inlet cross-section. When the state is high, the distortion is more obvious. At this time, the structure described in this patent has a partitioned multi-nozzle design, and adopts different flow gradient designs in the nozzle design to ensure that in a low state, when the incoming air temperature is higher than the engine's allowable range but slightly overheated, some injection points are injected in a small state to ensure the atomization effect of each injection point, thereby improving the evaporation efficiency and ensuring the jet effect in a small state. When the inlet state is high, the inlet duct temperature is high. At this time, opening all nozzles can also ensure the atomization of each injection point to ensure effective evaporation, heat absorption and cooling. This design can ensure that the jet liquid is well atomized throughout the entire working range. At the same time, for airflow distortion conditions, its partitioned and gradient flow design can effectively adjust the structure for effective cooling and temperature distribution, and can effectively ensure a good temperature field distribution at the outlet cross-section of the inlet jet section.

[0042] This application addresses the problem that when aerospace planes are in high Mach number flight, their inlet airflow distribution may be distorted, resulting in a higher intake pressure below the incoming air and uneven velocity distribution along the inlet cross-section. When the state is high, the distortion is more obvious. At this time, the structure described in this patent has a partitioned multi-nozzle design, and adopts different flow gradient designs in the nozzle design to ensure that in low state, when the incoming air temperature is higher than the engine allowable range but slightly overheated, some injection points are sprayed in a small state to ensure the atomization effect of each injection point, thereby improving the evaporation efficiency and ensuring the jet effect in a small state. When the inlet state is high, the inlet duct temperature is high. At this time, opening all nozzles can also ensure the atomization of each injection point to ensure effective evaporation, heat absorption and cooling. This design can ensure that the jet liquid is well atomized throughout the entire working range. At the same time, for the conditions of airflow distortion, its partitioned and gradient flow design can effectively adjust the structure for effective cooling and temperature distribution, and can effectively ensure a good temperature field distribution at the outlet cross-section of the inlet jet section.

[0043] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An aircraft engine jet cooling device, characterized in that: include: An air intake device (10) and a plurality of jet plates (20), the air intake device (10) comprising an upper wall surface, a lower wall surface, and two side walls, each jet plate (20) being installed between the upper wall surface and the lower wall surface, and the plurality of jet plates (20) being arranged at equal intervals on the same cross section of the air intake device (10); A plurality of vertical waterways are distributed on both sides of each jet plate (20), and a plurality of injection points are distributed at equal height intervals on each waterway. The same side of the jet plate is divided into a plurality of regions with gradually increasing areas from top to bottom, and nozzles of the same flow rate level are set at the injection points in each region; When the air intake volume is within a first preset range, the water channel on the jet plate (20) located at the front end in the airflow direction is opened; when the air intake volume is within a second preset range, every other water channel on the same side of the jet plate (20) is opened; and when the air intake volume is within a third preset range, all the water channels of the jet plate (20) are opened; The first preset range is smaller than the second preset range, and the second preset range is smaller than the third preset range; The angle between the direction of the water mist sprayed from the injection point and the incoming air intake direction is 90 degrees. The water mist sprayed from the injection point is an air cone structure, and the cone coverage angle is between 80-95 degrees. The injection points on the same side of the jet plate are staggered in height direction.

2. The aircraft engine jet cooling device according to claim 1, characterized in that: The conical water mist surfaces sprayed by two adjacent spray points in the vertical direction intersect.

3. The aircraft engine jet cooling device according to claim 1, characterized in that: The same side of the jet plate is divided into four areas from top to bottom, and the flow ratio of the nozzles in the four areas from top to bottom is 0.5:1:1.5:

2.

4. The aircraft engine jet cooling device according to claim 1, characterized in that: The ratio of the number of injection points in the four areas from top to bottom is 2:3:4:

6.

5. The aircraft engine jet cooling device according to claim 1, characterized in that: The water paths on both sides of the same jet plate (20) are arranged in a mirror image or staggered in the airflow direction.

6. The aircraft engine jet cooling device according to claim 1, characterized in that: The distance between adjacent jet plates (20) is greater than the thickness of the jet plates (20).

7. The aircraft engine jet cooling device according to claim 1, characterized in that: There is a certain distance between the uppermost nozzle of the jet plate (20) and the upper wall surface, and there is a certain distance between the lowermost nozzle and the lower wall surface, so that the water mist sprayed from the spray point will not be sprayed directly onto the wall surface.

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