Double-layer pipeline with leakage detection function, engine nacelle and aero-engine

Abstract

The utility model relates to the related technical field of aero-engines, in particular to a double-layer pipeline with a leakage detection function, an engine nacelle and an aero-engine, the double-layer pipeline comprising an outer pipeline and an inner pipeline is adopted for air entraining protection, and the reliability of a pipeline structure can be improved. Meanwhile, the air entraining pressure of the inner pipeline is monitored through the first pressure detection element, and the air entraining pressure in the interval between the outer pipeline and the inner pipeline is monitored through the second pressure detection element. Therefore, by monitoring the bleed air pressure of the inner pipeline and the bleed air pressure in the interval between the outer pipeline and the inner pipeline, the pressure values of the two positions can be obtained, and then whether bleed air leakage exists or not can be displayed through the numerical value change of the pressure values. The device can monitor the fracture condition of the pipeline in real time, the problem that a short hatch cover needs to be dismantled for regular detection is solved, and then the operation time and the labor cost can be reduced.

Description

Technical Field

[0001] This application relates to the technical field of aero-engines, specifically to double-layer piping with leak detection, engine nacelles, and aero-engines. Background Technology

[0002] Aircraft engine nacelle anti-icing typically uses high-pressure air from the engine compressor to prevent ice buildup in the engine intake that is detrimental to engine operation.

[0003] There are usually two to three baffles between the D-shaped cavity of the engine intake duct and the leading edge lip to prevent hot air from flowing backward. However, due to the presence of the baffles, it is usually not convenient to install overheat detection lines to monitor for leaks in the pipeline at this location.

[0004] Existing bleed air leak detection structures require opening the anti-icing vent cap of the engine nacelle to observe and determine if there is a bleed air leak. Furthermore, there is a possibility that internal and external pipes may rupture between two scheduled inspections without being detected in time. This can lead to the failure of the bleed air leak detection structure, which in turn will fail to detect the failure of the nacelle anti-icing system, potentially resulting in catastrophic consequences.

[0005] Therefore, there is an urgent need to design a double-layered pipeline, engine nacelle, and aero-engine with leak detection to solve the above-mentioned technical problems. Utility Model Content

[0006] This application provides a double-layered piping system with leak detection, an engine nacelle, and an aircraft engine, which can improve the detection of bleed air leaks.

[0007] To achieve the above objectives, in a first aspect, this application provides a double-layered pipeline with leak detection, comprising:

[0008] Internal piping;

[0009] An outer pipe is fitted around the outer periphery of the inner pipe and spaced apart from the inner pipe to form an annular gap, the two ends of which are sealed.

[0010] The first pressure detection element is used to monitor the bleed pressure of the inner pipeline;

[0011] The second pressure sensing element is used to monitor the bleed air pressure within the interval between the outer pipeline and the inner pipeline.

[0012] In some embodiments, the double-layer piping with leak detection further includes:

[0013] The first branch has one end connected to the inner pipeline and the other end extending out of the outer pipeline and connected to the first pressure detection element.

[0014] The second branch is located outside the external pipeline. One end of the second branch is connected to the external pipeline, and the other end is connected to the second pressure detection element.

[0015] In some embodiments, the anti-icing nozzle is connected to one end of the inner pipe of the double-layer pipeline, and the other end of the inner pipe is connected to the outlet port.

[0016] In some embodiments, the inner pipe is provided with an inlet, the outer pipe is provided with a clearance opening corresponding to the inlet, one end of the first branch is sealed to the inlet, the first branch passes through the clearance opening and is sealed to the outer pipe.

[0017] In some embodiments, a detection port is provided on the outer pipeline, and one end of the second branch is sealed to the detection port.

[0018] In some embodiments, the inner pipe is provided with an inlet, the outer pipe is provided with a clearance opening corresponding to the inlet, one end of the first branch is sealed to the inlet, the first branch passes through the clearance opening and is sealed to the outer pipe;

[0019] A detection port is provided on the outer pipeline, and one end of the second branch is sealed to the detection port;

[0020] The clearance opening and the detection opening are located on opposite sides of the external pipeline.

[0021] In some embodiments, both the first pressure sensing element and the second pressure sensing element are pressure sensors.

[0022] Secondly, this application also provides an engine nacelle, including the aforementioned double-layer piping with leak detection, and further comprising:

[0023] An air intake includes a leading edge lip and a front partition frame, wherein the front partition frame is disposed close to the leading edge lip and forms a front partition cavity with the leading edge lip;

[0024] The gas supply pipeline has an inlet port and an outlet port arranged opposite to each other, wherein the inlet port is used to connect to a high-temperature gas source;

[0025] An anti-icing nozzle is disposed within the front cavity and connected to the outlet port via the double-layer pipeline.

[0026] In some embodiments, the air intake duct further includes:

[0027] The rear partition is spaced apart from the front partition along the air intake direction of the air intake duct, and is located away from the leading edge lip relative to the front partition;

[0028] The double-layer pipeline is disposed in the gap between the front partition and the rear partition.

[0029] In some embodiments, the engine nacelle further includes:

[0030] An anti-icing valve is configured in the gas supply line for switching the opening and closing of the gas supply line;

[0031] The controller is electrically connected to the first pressure sensing element, the second pressure sensing element, and the anti-icing valve via wires.

[0032] In some embodiments, the anti-icing valve is located upstream of the double-layered piping with leak detection.

[0033] Thirdly, this application also provides an aircraft engine that includes the aforementioned engine nacelle.

[0034] The above-mentioned technical solution of this application has at least the following beneficial effects:

[0035] This application provides a double-layered piping system with leak detection, an engine nacelle, and an aero-engine. The system employs a double-layered piping system, including an outer and inner pipe, for bleed air protection, which improves the reliability of the piping structure. Simultaneously, this application monitors the bleed air pressure in the inner pipe using a first pressure detection element and the bleed air pressure in the gap between the outer and inner pipes using a second pressure detection element. Therefore, by monitoring the bleed air pressure in both the inner and outer pipes, pressure values ​​can be obtained at two points. Changes in these pressure values ​​can then indicate the presence of bleed air leakage. This system enables real-time monitoring of piping ruptures, avoiding the need for nacelle cover removal and periodic inspections, thus reducing operation time and labor costs. Attached Figure Description

[0036] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0037] Figure 1 This is a schematic diagram of the structure of the double-layer pipeline with leakage detection in the embodiments of this application;

[0038] Figure 2 This is a structural schematic diagram of the engine nacelle in an embodiment of this application;

[0039] Figure 3 This is an operational logic diagram of the engine nacelle in this embodiment of the application.

[0040] Explanation of reference numerals in the attached figures:

[0041] 10-Double-layer piping with leak detection; 100-Inner piping; 110-Inlet port; 200-Outer piping; 210-Breakout port; 220-Detection port; 230-Baffle; 300-First pressure detection element; 400-Second pressure detection element; 500-First branch; 600-Second branch; 20-Engine nacelle; 21-Inlet duct; 211-Leading edge lip; 212-Front bulkhead; 213-Front cavity; 214-Rear bulkhead; 22-Air supply piping; 221-Inlet port; 222-Outlet port; 23-Anti-icing nozzle; 24-Controller; 25-Anti-icing valve. Detailed Implementation

[0042] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0043] In the description of this application, it should be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", 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 element 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.

[0044] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, unless otherwise stated, "a plurality of" means two or more.

[0045] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection, a direct connection, or an indirect connection through an intermediate medium; or they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0046] This application provides a double-layered piping system with leak detection, an engine nacelle, and an aircraft engine, which are described in detail below. It should be noted that the order of description of the following embodiments is not intended to limit the preferred order of the embodiments of this application. Furthermore, the descriptions of each embodiment have their own emphasis; parts not described in detail in a certain embodiment can be referred to in the relevant descriptions of other embodiments.

[0047] Please see Figure 1 The embodiments of this application provide a double-layer pipeline 10 with leakage detection, including an inner pipeline 100, an outer pipeline 200, a first pressure detection element 300 and a second pressure detection element 400.

[0048] The outer pipe 200 is fitted around the outer periphery of the inner pipe 100 and spaced apart from the inner pipe 100, thereby forming an annular gap between the inner pipe 100 and the outer pipe 200, with both ends of the annular gap being sealed.

[0049] In this embodiment, a double-layer pipeline including an outer pipeline 200 and an inner pipeline 100 is used for air venting protection, which can improve the reliability of the pipeline structure.

[0050] Here, the first pressure sensing element 300 is used to monitor the bleed pressure of the inner pipe 100, and the second pressure sensing element 400 is used to monitor the bleed pressure in the interval between the outer pipe 200 and the inner pipe 100.

[0051] Therefore, by monitoring the bleed pressure of the inner pipeline 100 and the bleed pressure in the interval between the outer pipeline 200 and the inner pipeline 100, pressure values ​​at two locations can be obtained. Furthermore, by observing the changes in the pressure values, it can be shown whether there is a bleed leak.

[0052] Furthermore, since this application embodiment provides pressure measurement and monitoring inside the inner pipeline 100 and at the interlayer between the inner pipeline 100 and the outer pipeline 200, bleed air leakage can be detected in a timely manner. In particular, when this double-layer pipeline 10 with leakage detection is used for the engine nacelle 20, it can promptly indicate insufficient bleed air for nacelle anti-icing through pressure monitoring results, thereby preventing damage to the internal structure of the engine, avoiding damage to the engine blades caused by nacelle icing, and thus preventing catastrophic unannounced nacelle anti-icing function failure events.

[0053] Therefore, the double-layer pipeline 10 with leakage detection provided in this application embodiment can monitor the pipeline rupture in real time, avoiding the need to remove the hatch cover and conduct regular inspections, thereby reducing operation time and labor costs.

[0054] Here, the two ends of the annular gap can be made sealed. For example, see... Figure 1As shown, both ends of the outer pipe 200 are sealed by partitions 230. Of course, the partitions 230 can be sealed at both ends of the outer pipe 200 by welding or other methods. However, the inner pipe 100 is not sealed; under normal circumstances, bleed air passes through the inner pipe 100. Therefore, in the event of a leak in the inner pipe 100, the bleed air leaks into the outer pipe 200, while the outer pipe 200 can still supply bleed air, thus reducing the damage caused by the leak and allowing time for subsequent handling.

[0055] Furthermore, in some embodiments, the double-layer pipeline 10 with leakage detection provided in this application embodiment can be connected by two welding operations. That is, the inner pipeline 100 is first connected to a preset position by welding, such as between the anti-icing nozzle 23 and the outlet port 222 as described below, and then the outer pipeline 200 and the partition 230 are welded. The operation is very convenient, and the double-layer welding structure also improves the sealing performance.

[0056] In some embodiments, the double-layer piping 10 with leak detection further includes a first branch 500 and a second branch 600. One end of the first branch 500 is connected to the inner piping 100, and the other end extends outward from the outer piping 200 and connects to the first pressure sensing element 300. The second branch 600 is located outside the outer piping 200, with one end connected to the outer piping 200 and the other end connected to the second pressure sensing element 400.

[0057] With the above configuration, the first pressure detection element 300 can detect the bleed air pressure in the first branch 500, and the second pressure detection element 400 can detect the bleed air pressure in the interval between the outer pipe 200 and the inner pipe 100. In some embodiments, both the first pressure detection element 300 and the second pressure detection element 400 can be pressure sensors.

[0058] The first branch line 500 and the second branch line 600 can be made of high-temperature and high-pressure resistant materials to ensure stable and reliable operation in complex environments such as the engine intake manifold 21. Meanwhile, the connections between the first branch line 500 and the second branch line 600 and the inner pipe 100 and the outer pipe 200 are sealed using welding or sealing rings to prevent bleed air leakage and ensure the accuracy of pressure detection.

[0059] It is understandable that the upstream of this double-layered pipeline is usually connected to a single-layered pipeline, while the downstream of the double-layered pipeline connects to other components. Taking the first pressure detection unit as an example, if the first pressure detection unit is directly installed in the upstream single-layered pipeline and monitors the internal bleed pressure, the bleed pressure may vary at different locations in the pipeline, making it impossible to monitor the internal bleed pressure of the final section of the pipeline before other downstream components (i.e., the location of the double-layered pipeline in this application). In view of this, this application places the first pressure detection unit at the location of the first branch 500 connected to the inner pipeline 100 to achieve effective monitoring.

[0060] In some embodiments, based on the embodiment with the first branch 500, an inlet 110 may be provided on the inner pipe 100, and a clearance opening 210 corresponding to the inlet 110 may be provided on the outer pipe 200. One end of the first branch 500 is sealed to the inlet 110, and the first branch 500 passes through the clearance opening 210 and is sealed to the outer pipe 200.

[0061] With this configuration, the first branch 500 can pass through the outer conduit 200 and form an effective sealed connection with the inner conduit 100 within the outer conduit 200.

[0062] In some embodiments, based on the embodiment with a second branch 600, a detection port 220 is provided on the outer pipe 200, and one end of the second branch 600 is sealed to the detection port 220.

[0063] This setup allows for a sealed connection between the second branch 600 and the outer pipe 200 and inner pipe 100.

[0064] It is understood that the sealing connection in the embodiments of this application can be achieved by welding, or by setting a sealing ring or other means to prevent air leakage.

[0065] In some embodiments, where an inlet 110, a clearance port 210, and a detection port 220 are provided simultaneously, the clearance port 210 and the detection port 220 are located on opposite sides of the external pipeline 200 to prevent the first branch 500 and the second branch 600 from interfering with each other, and also to facilitate the assembly and maintenance of the overall structure.

[0066] To better achieve the technical effects of this application, please refer to Figure 2 The embodiments of this application also provide an engine nacelle 20, which includes a double-layered piping 10 with leak detection provided in any of the foregoing embodiments.

[0067] In addition, the engine nacelle 20 also includes an air intake 21, an air supply line 22, and an anti-icing nozzle 23.

[0068] The air intake duct 21 includes a leading edge lip 211 and a front partition 212. The front partition 212 is disposed close to the leading edge lip 211 and forms a front partition cavity 213 between it and the leading edge lip 211.

[0069] The gas supply line 22 has an inlet port 221 and an outlet port 222 that are provided opposite to each other. The inlet port 221 is used to connect to a high-temperature gas source.

[0070] An anti-icing nozzle 23 is disposed within the front cavity 213 and connected to the outlet port 222 via the double-layer pipeline.

[0071] In some embodiments, the anti-icing nozzle 23 is connected to one end of the inner pipe 100 of the double-layer pipeline, and the other end of the inner pipe 100 is connected to the outlet port 222. That is, the anti-icing nozzle 23 is connected to the outlet port 222 through the inner pipe 100 of the double-layer pipeline.

[0072] Here, since both ends of the outer pipe 200 are sealed, when the inner pipe 100 leaks, the outer pipe 200 can still maintain the airway connection between the anti-icing nozzle 23 and the outlet port 222, and the induced air can still enter the anti-icing nozzle 23 through the outer pipe 200, thus reserving time to deal with the leak in the inner pipe 100.

[0073] In some embodiments, the air intake duct 21 further includes a rear partition 214, which is spaced apart from the front partition 212 along the air intake direction of the air intake duct 21 and is disposed away from the leading edge lip 211 relative to the front partition 212.

[0074] The double-layer piping can be installed in the gap between the front bulkhead 212 and the rear bulkhead 214. This makes full use of the space inside the engine nacelle 20 while ensuring the installation stability and reliability of the double-layer piping.

[0075] In some embodiments, please refer to the following: Figure 3 The engine nacelle 20 also includes an anti-icing valve 25 and a controller 24.

[0076] The anti-icing valve 25 is installed on the gas supply line 22. The controller 24 is electrically connected to the first pressure detection element 300, the second pressure detection element 400, and the anti-icing valve 25 via wires.

[0077] Furthermore, according to a pre-set program, when the pressure values ​​detected by the first pressure detection element 300 and the second pressure detection element 400 meet preset conditions, the controller 24 controls the anti-icing valve 25 to open or close. For example, when the difference between the pressure values ​​detected by the first pressure detection element 300 and the second pressure detection element 400 is lower than a preset threshold, the controller 24 controls the anti-icing valve 25 to close. As another example, when the difference between the pressure values ​​detected by the first pressure detection element 300 and the second pressure detection element 400 is lower than a preset threshold, the controller 24 controls the anti-icing valve 25 to close, cutting off the bleed air supply to prevent insufficient anti-icing performance of the engine nacelle 20 or other damage to the engine due to bleed air leakage. Simultaneously, the controller 24 displays a system output pipeline leak alarm signal to the aircraft crew, reminding them to take appropriate measures in a timely manner.

[0078] Please see Figure 3 In practical applications, assuming a minor leak occurs in the inner pipe 100 of the double-layer piping system during flight, causing the bleed air pressure P1 in the inner pipe 100 to gradually decrease, the bleed air pressure P2 in the gap between the outer pipe 200 and the inner pipe 100 will also change accordingly. When the first pressure detection element 300 and the second pressure detection element 400 detect that the difference between P1 and P2, |P1-P2|, is less than a preset threshold M1, the controller 24 immediately determines that there is a leak in the double-layer piping system and quickly sends a signal C2 to close the anti-icing valve 25. In addition, the controller 24 can also send the leak alarm information C1 to the aircraft crew alarm display system so that the crew can be informed in time and take appropriate action. This can effectively avoid safety accidents caused by undetected bleed air leaks and ensure flight safety.

[0079] In some embodiments, the double-walled conduit 10 with leak detection is positioned near the end of the gas supply conduit 22, i.e., near the outlet port 222. For example, the double-walled conduit 10 with leak detection is positioned downstream of the anti-icing valve 25.

[0080] For example, the outlet port 222 of the aforementioned gas supply line 22 is connected to the inlet end of the double-layer line 10 with leak detection, and the outlet end of the double-layer line 10 with leak detection is connected to the anti-icing nozzle 23.

[0081] To better achieve the technical effects of the embodiments of this application, the embodiments of this application also provide an aircraft engine, which includes the engine nacelle 20 provided in any of the foregoing embodiments.

[0082] In the description of this specification, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0083] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of protection of the claims. Furthermore, specific examples have been used in the specification to illustrate the principles and implementation methods of this application. The description of the above embodiments is only for the purpose of helping to understand the method and core ideas of this application, and the content of this specification should not be construed as a limitation of this application.

Claims

1. A double-layer piping system with leak detection, characterized in that, include: Internal piping; An outer pipe is fitted around the outer periphery of the inner pipe and spaced apart from the inner pipe to form an annular gap, the two ends of which are sealed. The first pressure detection element is used to monitor the bleed pressure of the inner pipeline; The second pressure sensing element is used to monitor the bleed air pressure within the interval between the outer pipeline and the inner pipeline.

2. The double-layer pipeline with leak detection according to claim 1, characterized in that, Also includes: The first branch has one end connected to the inner pipeline and the other end extending out of the outer pipeline and connected to the first pressure detection element. The second branch is located outside the external pipeline. One end of the second branch is connected to the external pipeline, and the other end is connected to the second pressure detection element.

3. The double-layer pipeline with leak detection according to claim 2, characterized in that, The inner pipe is provided with an inlet, and the outer pipe is provided with a clearance opening corresponding to the inlet. One end of the first branch is sealed to the inlet, and the first branch passes through the clearance opening and is sealed to the outer pipe.

4. The double-layer pipeline with leak detection according to claim 2, characterized in that, A detection port is provided on the external pipeline, and one end of the second branch is sealed to the detection port.

5. The double-layer pipeline with leak detection according to claim 2, characterized in that, The inner pipe is provided with an inlet, and the outer pipe is provided with a clearance opening corresponding to the inlet. One end of the first branch is sealed to the inlet, and the first branch passes through the clearance opening and is sealed to the outer pipe. A detection port is provided on the outer pipeline, and one end of the second branch is sealed to the detection port; The clearance opening and the detection opening are located on opposite sides of the external pipeline.

6. The double-layer piping with leak detection according to any one of claims 1 to 5, characterized in that, Both the first pressure sensing element and the second pressure sensing element are pressure sensors.

7. An engine nacelle, characterized in that, include: Double-layer piping with leak detection as described in any one of claims 1 to 6; An air intake includes a leading edge lip and a front partition frame, wherein the front partition frame is disposed close to the leading edge lip and forms a front partition cavity with the leading edge lip; The gas supply pipeline has an inlet port and an outlet port arranged opposite to each other, wherein the inlet port is used to connect to a high-temperature gas source; An anti-icing nozzle is disposed within the front compartment and connected to the outlet port via a double-layered conduit with leakage detection.

8. The engine nacelle according to claim 7, characterized in that, The anti-icing nozzle is connected to one end of the inner pipe of the double-layered pipeline with leak detection, and the other end of the inner pipe is connected to the outlet port.

9. The engine nacelle according to claim 7, characterized in that, The air intake also includes: The rear partition is spaced apart from the front partition along the air intake direction of the air intake duct, and is located away from the leading edge lip relative to the front partition; The double-layer pipeline is disposed in the gap between the front partition and the rear partition.

10. The engine nacelle according to claim 7, characterized in that, include: An anti-icing valve is configured in the gas supply line for switching the opening and closing of the gas supply line; The controller is electrically connected to the first pressure sensing element, the second pressure sensing element, and the anti-icing valve via wires.

11. The engine nacelle according to claim 10, characterized in that, The anti-icing valve is located upstream of the double-layer pipeline with leak detection.

12. An aircraft engine, characterized in that, include: The engine nacelle as described in any one of claims 7 to 11.

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