Inlet strakes, aircraft engines, and aircraft

Abstract

This application provides an inlet support plate, an aero-engine, and an aircraft, relating to the field of aviation equipment technology. The inlet support plate includes: a plate body with a working fluid channel for circulating heat exchange working fluid; a working fluid inlet pipe disposed on the plate body, the inlet end of the working fluid channel being connected to the working fluid outlet end of an evaporator via the working fluid inlet pipe; and a working fluid outlet pipe disposed on the plate body, the outlet end of the working fluid channel being connected to the working fluid inlet end of an evaporator via the working fluid outlet pipe. The inlet support plate provided in this application can circulate the heat exchange working fluid in conjunction with the evaporator during use, absorbing heat from the heat exchange working fluid and reducing the amount of ice forming on the plate surface. While improving anti-icing capability, it eliminates the need for hot air supplied by the aero-engine compressor or the placement of heating devices on the plate surface, which helps reduce thrust loss and fuel consumption of the aero-engine and ensures the guiding capacity of the inlet support plate.

Description

Technical Field

[0001] This application relates to the field of aviation equipment technology, and in particular to an imported support plate, an aircraft engine, and an aircraft. Background Technology

[0002] Under the influence of high-speed, low-temperature airflow, the inlet support plate of an aero-engine is prone to surface icing, which deteriorates the inlet flow field of the aero-engine and affects the overall reliability and safety of the aero-engine and even the aircraft. In related technologies, to reduce the adverse effects of surface icing on the inlet support plate, hot gas anti-icing or electric heating anti-icing methods are commonly used to heat the inlet support plate.

[0003] However, since the high-temperature gas used in hot gas anti-icing mainly comes from the compressor of the aircraft engine, in order to ensure the heating effect on the inlet support plate, the compressor needs to provide a large amount of heat and air volume, which causes a large loss of thrust of the aircraft engine and increases the fuel consumption of the aircraft engine; while electrothermal anti-icing often requires heating elements to be attached to the surface of the inlet support plate, which can easily affect the airflow guiding effect of the inlet support plate. Summary of the Invention

[0004] This application aims to address at least one of the technical problems existing in the prior art or related technologies.

[0005] In view of this, a first aspect of the embodiments of this application provides an import support plate, comprising: The plate body has working fluid channels for the flow of heat exchange working fluid. The working fluid inlet pipe is installed on the plate body, and the inlet end of the working fluid channel is used to connect to the working fluid outlet end of the evaporator through the working fluid inlet pipe; The working fluid output pipe is installed on the plate, and the outlet end of the working fluid channel is used to connect to the working fluid input end of the evaporator through the working fluid output pipe.

[0006] In one feasible implementation, the cross-sectional area of ​​the working fluid channel decreases along the flow direction of the heat exchange working fluid.

[0007] In one feasible implementation, the working medium channel includes a straight channel section that extends along the length of the plate.

[0008] In one feasible implementation, the working medium channel further includes a curved channel section, and there are multiple straight channel sections. The multiple straight channel sections are arranged at intervals along the width direction of the plate, and adjacent straight channel sections are connected by a curved channel section.

[0009] In one feasible implementation, the ratio of the extension length of the straight channel segment to the length of the plate is greater than or equal to 0.85.

[0010] In one feasible implementation, the extension length of the working fluid channel is greater than or equal to five times the length of the plate; and / or The volume of the working medium channel is greater than or equal to 0.01 times the volume of the plate and less than or equal to 0.03 times the volume of the plate.

[0011] In one feasible implementation, the imported support plate further includes: The mounting base is located at one end of the plate along its length, and the working fluid input pipe and working fluid output pipe are located on the mounting base.

[0012] A second aspect of the embodiments of this application provides an aircraft engine, comprising: The casing has an air intake channel; The inlet support plate, as described in any of the first aspects above, is installed in the housing and located within the air intake passage; The evaporator has a working fluid inlet and a working fluid outlet. The inlet of the working fluid channel is connected to the working fluid outlet through a working fluid inlet pipe, and the outlet of the working fluid channel is connected to the working fluid inlet of the evaporator through a working fluid outlet pipe.

[0013] In one feasible implementation, the evaporator is a capillary evaporator; Wherein, the porosity of the capillary wick structure of the capillary wick evaporator is greater than or equal to 0.45 and less than or equal to 0.65; and / or The permeability of the capillary wick structure is greater than or equal to 0.5 × 10⁻⁶. -10 m 2 And less than or equal to 3 × 10 -10 m 2 .

[0014] A third aspect of the embodiments of this application provides an aircraft, comprising: As mentioned in any of the second aspects above, the aircraft engine is an example.

[0015] The above description is merely an overview of the technical solution provided in this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other features and effects of this application more obvious and easy to understand, the following are specific examples of the implementation methods of this application. Attached Figure Description

[0016] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of exemplary embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1A schematic structural diagram of the import support plate from a first-view perspective of one embodiment provided in this application; Figure 2 A schematic structural diagram of the imported support plate from a second perspective, provided for one embodiment of this application; Figure 3 for Figure 2 A schematic cross-sectional view of the inlet support plate along the AA direction is shown; Figure 4 for Figure 3 A schematic enlarged view of a portion of region B in the middle; Figure 5 A schematic diagram showing the connection relationship between the inlet support plate and the evaporator in one embodiment of this application.

[0017] in, Figures 1 to 5 The correspondence between the reference numerals and component names in the attached drawings is as follows: 100. Imported support plate; 110. Plate body; 120. Working fluid inlet pipe; 130. Working fluid outlet pipe; 140. Mounting base; 200. Evaporator; 1101, working medium channel; 1101a, straight channel section; 1101b, curved channel section. Detailed Implementation

[0018] Exemplary embodiments of the present application will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present application are shown in the drawings, it should be understood that the present application can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this application will be thorough and complete, and will fully convey the scope of the present application to those skilled in the art.

[0019] like Figures 1 to 5 As shown, according to a first aspect of the embodiments of this application, an inlet support plate 100 is provided, comprising: a plate body 110, having a working fluid channel 1101 for circulating heat exchange working fluid; a working fluid inlet pipe 120 disposed on the plate body 110, the inlet end of the working fluid channel 1101 being connected to the working fluid outlet end of the evaporator 200 through the working fluid inlet pipe 120; and a working fluid outlet pipe 130 disposed on the plate body 110, the outlet end of the working fluid channel 1101 being connected to the working fluid inlet end of the evaporator 200 through the working fluid outlet pipe 130.

[0020] The inlet support plate 100 provided in this application includes the aforementioned plate body 110, working fluid inlet pipe 120, and working fluid outlet pipe 130. The plate body 110 has an internal working fluid channel 1101 for the flow of the heat exchange working fluid. Both the working fluid inlet pipe 120 and the working fluid outlet pipe 130 are mounted on the plate body 110. One end of the working fluid inlet pipe 120 is connected to the inlet end of the working fluid channel 1101, and the other end can be connected to the working fluid outlet end of the evaporator 200. One end of the working fluid outlet pipe 130 is connected to the outlet end of the working fluid channel 1101, and the other end, in practical applications, can be connected to the working fluid inlet end of the evaporator 200. Thus, during the use of the inlet support plate 100, the working fluid channel 1101 can receive the high-temperature heat exchange working fluid output from the evaporator 200 through the working fluid inlet pipe 120. After the high-temperature heat exchange working fluid flows into the working fluid channel 1101, the plate body 110 can absorb heat. The heat of the working fluid raises the temperature of plate 110, thereby melting the frost that has formed on the surface of plate 110 and reducing the amount of ice formation on the surface of plate 110 during the operation of the aero-engine. This helps to ensure the inlet flow field state of the aero-engine and provides a guarantee for the safe and stable operation of the aero-engine and the aircraft. Correspondingly, the heat exchange working fluid after heat exchange with plate 110 can flow back to evaporator 200 through working fluid output pipe 130 to absorb heat again, which facilitates the circulation of the heat exchange working fluid. Furthermore, based on the aforementioned configuration, the inlet support plate 100 can improve the anti-icing capability without the need for the compressor of the aero-engine to provide hot air or to place heating devices on the surface of plate 110. This helps to reduce the thrust loss and fuel consumption of the aero-engine and ensure the flow guiding capability of the inlet support plate 100.

[0021] It is understood that the inlet support plate 100 provided in this application can be installed in an aero-engine or used as a component of an aero-engine in practical applications. Specifically, the inlet support plate 100 can be used as an inlet structural component of an aero-engine. In practical applications, the inlet support plate 100 can be installed in the aero-engine housing and located within the air intake passage of the housing. The inlet support plate 100 can be arranged corresponding to the inlet end of the aforementioned air intake passage to guide and rectify the air intake of the aero-engine; for example, such as Figures 1 to 4 As shown, Figure 3 and Figure 4 The L direction is used to schematically represent the length direction of the plate 110, and the W direction is used to schematically represent the width direction of the plate 110. At least one of the two ends in the length direction of the plate 110 can be used to fix and connect the aforementioned housing. The two ends in the width direction of the plate 110 are the front edge and the rear edge of the plate 110, respectively. The thickness of the rear edge is greater than the thickness of the front edge. During use, the front edge can serve as the windward side of the plate 110.

[0022] It is understandable that the inlet support plate 100 can be connected to the evaporator 200 through the aforementioned working fluid inlet pipe 120 and working fluid outlet pipe 130, such as... Figure 5 As shown, when the inlet support plate 100 is connected to the evaporator 200, it can cooperate with the evaporator 200 to form a circulation path for the heat exchange medium. The heat exchange medium can absorb heat during the process of flowing through the evaporator 200, so as to heat the plate 110 after circulating to the aforementioned medium channel 1101. The aforementioned evaporator 200 can be the evaporator 200 of the aircraft's air conditioning system or loop heat pipe system. Alternatively, in practical applications, an independent evaporator 200 can be configured for the inlet support plate 100. When the inlet support plate 100 is connected to the independently configured evaporator 200, the evaporator 200 can be heat-transfer connected to the heat-generating parts of the aircraft engine or the heat-generating components of the aircraft to absorb the heat from the aforementioned heat-generating parts or components to heat the heat exchange medium. This enables the utilization of waste heat from the aircraft engine or aircraft, further saving energy consumption during the anti-icing process of the inlet support plate 100. When the aforementioned evaporator 200 is the evaporator 200 of the aircraft's air conditioning system or loop heat pipe system, the installation cost of the evaporator 200 can be reduced, thereby lowering the modification cost of the aircraft engine or aircraft.

[0023] It is understood that the aforementioned heat exchange medium can be a phase change heat exchange medium, such as, but not limited to, ammonia. Taking ammonia as the heat exchange medium as an example, in practical applications, the evaporator 200 can be used to output gaseous ammonia at a higher temperature. As the gaseous ammonia flows through the working medium channel 1101, it gradually releases heat and transforms into liquid ammonia at a lower temperature. During the phase change, ammonia can generate significant heat absorption or release, which helps improve the heating efficiency of the heat exchange medium on the plate 110, reduces the amount of heat exchange medium used, and enhances the anti-icing and de-icing effect on the plate 110. Correspondingly, the aforementioned plate 110, working medium inlet pipe 120, and working medium outlet pipe 130 can be made of corrosion-resistant materials, which helps extend the service life of the inlet support plate 100. For example, the plate 110, the working fluid inlet pipe 120, and the working fluid outlet pipe 130 can be made of high-strength corrosion-resistant materials such as stainless steel, nickel-based alloys, or titanium alloys. For instance, the plate 110, the working fluid inlet pipe 120, and the working fluid outlet pipe 130 can be made of 316L stainless steel, which helps to enhance the structural stability and reliability of the inlet support plate 100 while ensuring its resistance to ammonia.

[0024] In some feasible examples, the plate 110 can be 3D printed, which can save material consumption when making the plate 110 and improve the processing accuracy and production efficiency of the plate 110.

[0025] In some feasible examples, the aforementioned working fluid inlet pipe 120 and the aforementioned working fluid outlet pipe 130 can be an integral structure with the plate body 110 or both can be sealed and connected to the plate body 110, thereby avoiding leakage of the heat exchange working fluid in the inlet support plate 100.

[0026] In some feasible examples, the aforementioned working fluid input pipe 120 and the aforementioned working fluid output pipe 130 can be located at the same end in the length direction of the plate 110, thereby allowing the parts of the inlet support plate 100 used for docking with the external structure to be centrally distributed, which is beneficial to improving the structural compactness of the inlet support plate 100.

[0027] like Figure 3 and Figure 4 As shown, in one feasible implementation, the cross-sectional area of ​​the working fluid channel 1101 decreases along the flow direction of the heat exchange working fluid.

[0028] In this technical solution, the working medium channel 1101 can be gradually narrowed along the flow direction of the heat exchange medium, which can promote the accelerated flow of the heat exchange medium from the inlet end to the outlet end of the working medium channel 1101. This can compensate for the flow velocity loss caused by the gradual increase of the gas-liquid ratio during the flow of the heat exchange medium, thereby ensuring the heat exchange efficiency between the heat exchange medium and the plate 110 during the flow of the heat exchange medium through the working medium channel 1101. It can also prevent the heat exchange medium from releasing heat in the upstream section of the working medium channel 1101, reduce the heating dead zone on the plate 110, improve the heat utilization efficiency of the plate 110 for the heat exchange medium, enhance the anti-icing effect of the inlet support plate 100, and also ensure the heat release liquefaction efficiency of the heat exchange medium. This can also prevent a large amount of gaseous heat exchange medium from flowing back to the evaporator 200 before heat release liquefaction, which is conducive to ensuring the operational stability of the evaporator 200 and reducing the failure risk of the evaporator 200.

[0029] It is understandable that the flow direction of the heat exchange medium is the axial extension direction of the medium channel 1101 from the inlet end to the outlet end, and the cross-sectional area of ​​the aforementioned medium channel 1101 is the cross-sectional area of ​​the medium channel 1101 perpendicular to its axis.

[0030] It is understood that the cross-sectional area of ​​the aforementioned working medium channel 1101 can be continuously reduced along the flow direction of the heat exchange working medium, or reduced in stages along the flow direction of the heat exchange working medium. The specific reduction method of the cross-section can be set according to actual needs, and no further restrictions are imposed here.

[0031] It is understandable that the inner diameter of the working medium input pipe 120 is larger than the inner diameter of the working medium output pipe 130, so that the cross-sectional area of ​​the internal space of the working medium input pipe 120 and the working medium output pipe 130 can be matched with the cross-sectional area of ​​the inlet end and the outlet end of the working medium channel 1101, respectively.

[0032] like Figure 3 and Figure 4 As shown, in one feasible embodiment, the working medium channel 1101 includes a straight channel section 1101a, which extends along the length direction of the plate 110.

[0033] In this technical solution, the working fluid channel 1101 may include the aforementioned straight channel section 1101a. Based on the aforementioned configuration, the heat exchange channel can utilize the straight channel section 1101a to ensure smooth flow of the heat exchange working fluid along the length direction of the plate 110, reduce pressure loss of the heat exchange working fluid during the flow process, expand the heating range of the heat exchange working fluid along the length direction of the plate 110, reduce heating dead zones on the plate 110, and ensure the anti-icing and de-icing effect of the plate 110.

[0034] It is understandable that the two ends of the straight channel section 1101a are connected to the working fluid input pipe 120 and the working fluid output pipe 130, respectively.

[0035] like Figure 3 and Figure 4 As shown, in one feasible embodiment, the working medium channel 1101 further includes a curved channel section 1101b, and there are multiple straight channel sections 1101a. The multiple straight channel sections 1101a are arranged at intervals along the width direction of the plate 110, and two adjacent straight channel sections 1101a are connected by the curved channel section 1101b.

[0036] In this technical solution, the working medium channel 1101 may also include the aforementioned curved channel section 1101b. Two adjacent straight channel sections 1101a in the width direction of the plate 110 can be connected through the aforementioned curved channel section 1101b, so that the working medium channel 1101 can extend in a serpentine or winding manner, which can further expand the distribution range of the working medium channel 1101 on the plate 110, increase the heat exchange area between the heat exchange medium and the plate 110, and help improve the heating effect of the heat exchange medium on the plate 110 and enhance the anti-icing capability of the inlet support plate 100.

[0037] It is understandable that there can be multiple curved channel sections 1101b. Multiple straight channel sections 1101a and multiple curved channel sections 1101b can be arranged alternately along the flow direction of the heat exchange medium, so that the medium channel 1101 extends in a serpentine shape as a whole.

[0038] In one feasible implementation, the ratio of the extension length of the straight channel segment 1101a to the length of the plate 110 is greater than or equal to 0.85.

[0039] In this technical solution, the ratio of the extension length of the straight channel section 1101a to the length of the plate 110 can be greater than or equal to 0.85. Based on the aforementioned setting, the distribution range of the straight channel section 1101a along the length of the plate 110 can be relatively large, thereby allowing the heat exchange medium to exchange heat with different parts along the length of the plate 110. This is beneficial for improving the temperature uniformity of the plate 110 along its length, avoiding excessive temperature differences between the two ends of the plate 110 along its length, reducing heating dead zones on the plate 110, and improving the anti-icing and de-icing effects of the plate 110.

[0040] It is understandable that the extension length of the straight channel segment 1101a is also the length of the straight channel segment 1101a in the length direction of the plate 110.

[0041] For example, the ratio of the extension length of the straight channel segment 1101a to the length of the plate 110 can be, but is not limited to, 0.85, 0.88, 0.9, 0.92 or 0.95.

[0042] In one feasible implementation, the extension length of the working fluid channel 1101 is greater than or equal to five times the length of the plate 110; and / or The volume of the working medium channel 1101 is greater than or equal to 0.01 times the volume of the plate 110 and less than or equal to 0.03 times the volume of the plate 110.

[0043] In this technical solution, the extension length of the working medium channel 1101 can be set to be greater than or equal to 5 times the length of the plate 110, thereby extending the flow distance of the heat exchange medium in the working medium channel 1101, increasing the heat absorption of the plate 110 during the heating process, improving the heat absorption efficiency of the plate 110 for the heat exchange medium, ensuring the anti-icing capability of the plate 110, and preventing the phenomenon of a large amount of gaseous heat exchange medium flowing back to the evaporator 200, which is conducive to ensuring the operational stability of the evaporator 200.

[0044] In this technical solution, the volume of the working fluid channel 1101 can be set to be greater than or equal to 0.01 times the volume of the plate 110 and less than or equal to 0.03 times the volume of the plate 110. This can, on the one hand, prevent the volume of the working fluid channel 1101 from being too small, so that the plate 110 can accommodate a relatively large amount of heat exchange working fluid during use, which is beneficial to ensuring the heat absorption of the plate 110 during the heating process and can increase the heat exchange area between the heat exchange working fluid and the plate 110, thereby improving the heating efficiency of the heat exchange working fluid on the plate 110. On the other hand, it can also prevent the volume of the working fluid channel 1101 from being too large, which can reduce the weakening of the structural strength of the plate 110 by the working fluid channel 1101 and help ensure the structural reliability and stability of the plate 110.

[0045] It is understood that the extension length of the working medium channel 1101 is the extension length of the axis of the working medium channel 1101 from the inlet end to the outlet end. When the working medium channel 1101 includes the aforementioned straight channel section 1101a and curved channel section 1101b, the extension length of the working medium channel 1101 is the sum of the extension lengths of all straight channel sections 1101a and all curved channel sections 1101b.

[0046] It is understandable that in this technical solution, while setting the extension length of the working medium channel 1101 to be greater than or equal to 5 times the length of the plate 110, the volume of the working medium channel 1101 can be greater than or equal to 0.01 times the volume of the plate 110 and less than or equal to 0.03 times the volume of the plate 110.

[0047] Understandably, in practical applications, the extension form of the working medium channel 1101 can be specifically set according to actual needs, so that the extension length of the working medium channel 1101 is greater than 5 times the length of the plate 110. For example, the working medium channel 1101 can be set to extend in a serpentine, coiled or spiral shape, or the extension form of the working medium channel 1101 can be determined based on topology optimization so that the extension length of the working medium channel 1101 can be greater than 5 times the length of the plate 110.

[0048] For example, the extension length of the working fluid channel 1101 can be, but is not limited to, 5 times, 6 times, 8 times, 10 times or 12 times the length of the plate 110.

[0049] For example, the volume of the working medium channel 1101 can be, but is not limited to, 0.01 times, 0.015 times, 0.02 times, 0.025 times, or 0.03 times the volume of the plate 110.

[0050] like Figures 1 to 3 As shown, in one feasible embodiment, the inlet support plate 100 further includes: a mounting base 140 disposed at one end of the plate body 110 in the length direction, and a working fluid input pipe 120 and a working fluid output pipe 130 disposed on the mounting base 140.

[0051] In this technical solution, the inlet support plate 100 may further include the aforementioned mounting base 140. Based on the aforementioned configuration, the inlet support plate 100 can utilize the mounting base 140 to fix the working propellant input pipe 120 and the working propellant output pipe 130, thereby improving the installation stability of the working propellant input pipe 120 and the working propellant output pipe 130, reducing the risk of the working propellant input pipe 120 and the working propellant output pipe 130 falling off during use, and in practical applications, the mounting base 140 can also be used to connect to the housing of the aircraft engine, thereby achieving the fixation of the inlet support plate 100 on the aforementioned housing and improving the installation stability of the inlet support plate 100.

[0052] Understandably, in practical applications, the mounting base 140 can be fixed to the housing by bolt connection. Accordingly, bolt holes can be provided on the mounting base 140 to facilitate the insertion of bolts.

[0053] Understandably, based on the aforementioned mounting base 140, the parts of the inlet support plate 100 used for docking with the external structure can be centrally distributed, which is beneficial to improving the structural compactness of the inlet support plate 100.

[0054] In some feasible examples, the thickness of plate 110 is greater than or equal to 1.5 mm, which can ensure the structural strength of plate 110 and provide assurance for the load-bearing capacity and vibration performance of the inlet support plate 100.

[0055] According to a second aspect of the embodiments of this application, an aero-engine is provided, comprising: a housing having an air intake passage; an inlet support plate 100 as described in any of the first aspects above, disposed on the housing and located within the air intake passage; and an evaporator 200 having a working fluid input end and a working fluid output end, wherein the inlet end of a working fluid passage 1101 is connected to the working fluid output end via a working fluid input pipe 120, and the outlet end of the working fluid passage 1101 is connected to the working fluid input end of the evaporator 200 via a working fluid output pipe 130.

[0056] The aero-engine provided in this application includes the aforementioned housing, evaporator 200, and inlet support plate 100 as described in any of the first aspects above. The inlet support plate 100 is mounted on the engine casing and located within the air intake channel of the casing, facilitating the guidance and rectification of the air intake for the aero-engine. The inlet support plate 100 includes a plate body 110, a working fluid inlet pipe 120, and a working fluid outlet pipe 130. The plate body 110 has a working fluid channel 1101 for circulating the heat exchange working fluid. Both the working fluid inlet pipe 120 and the working fluid outlet pipe 130 are mounted on the plate body 110. One end of the working fluid inlet pipe 120 is connected to the inlet end of the working fluid channel 1101, and the other end is connected to the working fluid outlet end of the evaporator 200. One end of the working fluid outlet pipe 130 is connected to the outlet end of the working fluid channel 1101, and the other end is connected to the working fluid inlet end of the evaporator 200. Thus, during the use of the inlet support plate 100, the working fluid channel 1101 can access the heat exchange working fluid output from the evaporator 200 at a higher temperature via the working fluid inlet pipe 120. After the heat exchange medium with a higher temperature flows into the working medium channel 1101, the plate 110 can absorb the heat of the heat exchange medium to raise the temperature of the plate 110. This will help melt the frost that has formed on the surface of the plate 110, reduce the amount of ice on the surface of the plate 110 during the operation of the aero-engine, and help ensure the inlet flow field state of the aero-engine. This will provide a guarantee for the safe and stable operation of the aero-engine and the aircraft. Correspondingly, the heat exchange medium after exchanging heat with the plate 110 can flow back to the evaporator 200 through the working medium output pipe 130 to absorb heat again, which facilitates the circulation of the heat exchange medium. Furthermore, based on the aforementioned configuration, the inlet support plate 100 can improve the anti-icing capability without the need for the compressor of the aero-engine to provide hot air or to place heating devices on the surface of the plate 110. This will help reduce the thrust loss and fuel consumption of the aero-engine and ensure the flow guiding capability of the inlet support plate 100.

[0057] It is understandable that, such as Figures 1 to 4 As shown, at least one of the two ends of the plate 110 in the length direction can be used to fix the aforementioned housing. The two ends of the plate 110 in the width direction are the front edge and the rear edge of the plate 110, respectively. The thickness of the rear edge is greater than the thickness of the front edge. During use, the front edge can serve as the windward side of the plate 110.

[0058] Understandably, the inlet support plate 100 can cooperate with the evaporator 200 to form a circulating flow path for the heat exchange medium. The heat exchange medium absorbs heat as it flows through the evaporator 200, so that it can heat the plate 110 after circulating to the aforementioned medium channel 1101. The evaporator 200 can be connected to the heat-generating parts of the aero-engine or aircraft to absorb heat from these parts and heat the heat exchange medium, thereby enabling the utilization of waste heat from the aero-engine or aircraft and further saving energy consumption during the anti-icing process of the inlet support plate 100.

[0059] For example, the aforementioned aero-engine may also include a compressor and a lubricating oil system. The evaporator 200 may be heat-transfer connected to the compressor housing, the lubricating oil radiator housing of the lubricating oil system, or the outer wall of the lubricating oil system pipeline. Thus, the evaporator 200 can use the waste heat of the compressor or the lubricating oil system to heat the heat exchange working fluid. Compared with the hot gas de-icing method, it can avoid directly drawing air from the compressor, which is beneficial to reducing the thrust loss of the engine.

[0060] For example, the evaporator 200 can be heat-transfer connected to electronic devices such as the power supply and frequency converter of the aircraft that generate a large amount of heat during operation, so as to use the waste heat of the aforementioned electronic devices to heat the heat exchange medium.

[0061] It is understood that the aforementioned heat exchange medium can be a phase change heat exchange medium, such as, but not limited to, ammonia. Taking ammonia as the heat exchange medium as an example, in practical applications, the evaporator 200 can be used to output gaseous ammonia at a higher temperature. As the gaseous ammonia flows through the working medium channel 1101, it gradually releases heat and transforms into liquid ammonia at a lower temperature. During the phase change, ammonia can generate significant heat absorption or release, which helps improve the heating efficiency of the heat exchange medium on the plate 110, reduces the amount of heat exchange medium used, and enhances the anti-icing and de-icing effect on the plate 110. Correspondingly, the aforementioned plate 110, working medium inlet pipe 120, and working medium outlet pipe 130 can be made of corrosion-resistant materials, which helps extend the service life of the inlet support plate 100. For example, the plate 110, the working fluid inlet pipe 120, and the working fluid outlet pipe 130 can be made of high-strength corrosion-resistant materials such as stainless steel, nickel-based alloys, or titanium alloys. For instance, the plate 110, the working fluid inlet pipe 120, and the working fluid outlet pipe 130 can be made of 316L stainless steel, which helps to enhance the structural stability and reliability of the inlet support plate 100 while ensuring its resistance to ammonia.

[0062] In one feasible embodiment, the evaporator 200 is a capillary evaporator; wherein the porosity of the capillary structure of the capillary evaporator is greater than or equal to 0.45 and less than or equal to 0.65; and / or The permeability of the capillary wick structure is greater than or equal to 0.5 × 10⁻⁶. -10m 2 And less than or equal to 3 × 10 -10 m 2 .

[0063] In this technical solution, the evaporator 200 can be a capillary evaporator. In practical applications, the evaporator 200 can use the capillary force of its capillary structure to drive the heat exchange medium to circulate, which can reduce the driving energy consumption of the heat exchange medium. Moreover, the capillary evaporator has a compact structure and relatively small size and weight, which makes it easy to install and arrange in practical applications. This can improve the installation convenience of the evaporator 200 and reduce the overall installation difficulty of the aero-engine.

[0064] The porosity of the capillary wick structure can be set to be greater than or equal to 0.45 and less than or equal to 0.65, which can ensure that the capillary wick structure has good fluid storage capacity and avoid the capillary force generated by the capillary wick structure being too low. This is beneficial to ensuring the heat exchange performance of the capillary wick evaporator and the driving efficiency of the heat exchange medium.

[0065] The permeability of the capillary wick structure can be set to be greater than or equal to 0.5 × 10⁻⁶. -10 m 2 And less than or equal to 3 × 10 - 10 m 2 This avoids excessive flow resistance or low suction capacity of the heat exchange medium in the capillary structure, which helps to ensure the heat exchange performance and driving efficiency of the heat exchange medium in the capillary evaporator.

[0066] It is understandable that in this technical solution, the porosity of the capillary wick structure can be set to be greater than or equal to 0.45 and less than or equal to 0.65, while the permeability of the capillary wick structure can be set to be greater than or equal to 0.5 × 10⁻⁶. -10 m 2 And less than or equal to 3 × 10 -10 m 2 .

[0067] For example, the porosity of the capillary wick structure can be, but is not limited to, 0.45, 0.5, 0.55, 0.6, or 0.65.

[0068] For example, the permeability of the capillary wick structure can be, but is not limited to, 0.5 × 10⁻⁶. -10 m 2 1.0×10 -10 m 2 1.5×10 -10 m 2 2.5×10 -10 m 2 Or 3×10 -10 m 2 wait.

[0069] It should be noted that in practical applications, capillary evaporators can have multiple liquid reservoirs, all of which are connected to the capillary structure and arranged in different positions of the capillary structure, thereby reducing the impact of the attitude changes of the aero-engine on the operational stability of the capillary evaporator; the structural form of the capillary evaporator can be, but is not limited to, cylindrical or flat plate.

[0070] Furthermore, since the aero-engine provided in this application embodiment includes the inlet support plate 100 as proposed in any of the first aspects above, it possesses all the beneficial effects of the inlet support plate 100, which will not be elaborated here.

[0071] A third aspect of the embodiments of this application provides for an aircraft comprising: an aero-engine as described in any of the second aspects above.

[0072] Since the aircraft provided in this application includes an aero-engine as described in any of the second aspects above, it possesses all the beneficial effects of such an aero-engine, which will not be elaborated here.

[0073] In this application, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance; the term "multiple" refers to two or more unless otherwise expressly defined. The terms "install," "connect," "link," and "fix" should be interpreted broadly. For example, "connect" can mean a fixed connection, a detachable connection, or an integral connection; "link" can mean a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0074] In the description of this application, it should be understood that the terms "upper", "lower", "left", "right", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or unit referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0075] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0076] The above are merely preferred embodiments of this application and are not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. An imported support plate, characterized in that, include: The plate body has a working fluid channel for circulating the heat exchange working fluid. A working fluid input pipe is disposed on the plate body, and the inlet end of the working fluid channel is used to connect to the working fluid output end of the evaporator through the working fluid input pipe; A working fluid output pipe is disposed on the plate body, and the outlet end of the working fluid channel is used to connect to the working fluid input end of the evaporator through the working fluid output pipe.

2. The imported support plate according to claim 1, characterized in that, The cross-sectional area of ​​the working fluid channel decreases along the flow direction of the heat exchange working fluid.

3. The imported support plate according to claim 1, characterized in that, The working medium channel includes a straight channel section that extends along the length of the plate.

4. The imported support plate according to claim 3, characterized in that, The working medium channel also includes a curved channel section, and there are multiple straight channel sections. The multiple straight channel sections are arranged at intervals along the width direction of the plate, and two adjacent straight channel sections are connected by the curved channel section.

5. The imported support plate according to claim 3, characterized in that, The ratio of the extension length of the straight channel section to the length of the plate is greater than or equal to 0.

85.

6. The imported support plate according to any one of claims 1 to 5, characterized in that, The extension length of the working fluid channel is greater than or equal to 5 times the length of the plate; and / or The volume of the working medium channel is greater than or equal to 0.01 times the volume of the plate and less than or equal to 0.03 times the volume of the plate.

7. The imported support plate according to any one of claims 1 to 5, characterized in that, Also includes: A mounting base is provided at one end of the plate along its length, and the working fluid input pipe and the working fluid output pipe are provided on the mounting base.

8. An aircraft engine, characterized in that, include: The casing has an air intake channel; The inlet support plate as described in any one of claims 1 to 7 is disposed in the housing and located within the air intake channel; An evaporator has a working fluid input end and a working fluid output end. The inlet end of the working fluid channel is connected to the working fluid output end through the working fluid input pipe, and the outlet end of the working fluid channel is connected to the working fluid input end of the evaporator through the working fluid output pipe.

9. The aero-engine according to claim 8, characterized in that, The evaporator is a capillary evaporator; Wherein, the porosity of the capillary wick structure of the capillary wick evaporator is greater than or equal to 0.45 and less than or equal to 0.65; and / or The permeability of the capillary wick structure is greater than or equal to 0.5 × 10⁻⁶. -10 m 2 And less than or equal to 3 × 10 -10 m 2 .

10. An aircraft, characterized in that, include: The aircraft engine as described in claim 8 or 9.

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