An online real-flow test device and method for aircraft high-temperature and high-pressure valve leakage

Abstract

This application relates to the field of aircraft valve leakage testing technology, specifically disclosing an online real-flow testing method for the leakage of aircraft high-temperature and high-pressure valves. The online real-flow testing device for the leakage of aircraft high-temperature and high-pressure valves includes an air inlet pipe, a leaking gas collection box, an air outlet pipe, an ambient temperature sensor, a leaking gas exhaust pipe, a cooling device, an exhaust temperature sensor, and a flow meter. The high-temperature and high-pressure valve is installed in the leaking gas collection box, connected by the air inlet and outlet pipes. Hot air at various temperatures simulating the valve's operation is introduced through the air inlet pipe. The leaking gas collection box uses cooling components on its walls to control the ambient temperature simulating the valve's operation. The leaking gas enters the leaking gas exhaust pipe, and the cooling device cools the leaking gas to room temperature. The flow meter displays the leaking gas flow rate. This method can realistically reflect the impact of the high-temperature and high-pressure air produced during the entire engine start-up process on the valve leakage.

Description

Technical Field

[0001] This application relates to the field of aircraft valve leakage testing technology, specifically to an online actual flow testing device and method for aircraft high temperature and high pressure valve leakage. Background Technology

[0002] High-pressure bleed air valves, pressure regulating / shut-off valves, and precooler regulating valves in aircraft air supply systems are key components of the aircraft environmental control system. Operating in the high-temperature, vibrating environment of the aircraft engine nacelle, they have a relatively high failure rate. These valves employ electromagnetic control and pneumatic operation, are large in size and complex in structure, and have numerous functional exhaust ports and inherent leakage points. Excessive leakage can, at best, affect system performance, and at worst, raise the temperature of the surrounding structure, posing a threat to flight safety. During aircraft accessory production or maintenance, the leakage rate of high-temperature, high-pressure valves is a mandatory inspection item. However, testing is generally conducted using room-temperature gas, which cannot accurately reflect the impact of thermal expansion caused by high temperatures during normal operation on the leakage rate. Summary of the Invention

[0003] Since the leakage of high-temperature and high-pressure valves is detected using room-temperature gas, it cannot accurately reflect the impact of thermal expansion caused by high temperature on the leakage during normal operation. Therefore, this application proposes the following improvement scheme.

[0004] In the first aspect, this application proposes an online actual flow test device for the leakage of high temperature and high pressure valves in aircraft, and adopts the following technical solution.

[0005] An online real-flow testing device for the leakage of an aircraft high-temperature and high-pressure valve includes an air inlet pipe, a leak gas collection box, an air outlet pipe, an ambient temperature sensor, a leak gas exhaust pipe, a cooling device, an exhaust temperature sensor, and a flow meter.

[0006] The leaking gas collection box has internal space for installing high-temperature, high-pressure valves. The collection box has three openings, with the others closed. The first opening is seamlessly connected to the air inlet pipe, the second to the air outlet pipe, and the third to the leaking gas exhaust pipe. Cooling components are installed on the walls of the collection box.

[0007] The air inlet pipe is inserted into the leaked gas collection box to connect to the air inlet of the high-temperature, high-pressure valve. The air outlet pipe is inserted into the leaked gas collection box to connect to the air outlet of the high-temperature, high-pressure valve.

[0008] The ambient temperature sensor is installed in the third port.

[0009] The cooling device acts on a section of the leaking gas exhaust pipe. The exhaust temperature sensor is installed in the section of the leaking gas exhaust pipe downstream of the cooling device. The flow meter is installed in the section of the leaking gas exhaust pipe downstream of the exhaust temperature sensor.

[0010] By adopting the above technical solution, a high-temperature, high-pressure valve can be installed in a leaky gas collection box. An air inlet pipe and an air outlet pipe connect to the valve. Hot air simulating the normal ventilation temperature of the valve is introduced through the air inlet pipe. The leaky gas collection box collects the gas leaking from the valve. Cooling components on the box walls control the ambient temperature around the valve, simulating the temperature during valve operation. The leaked gas discharged from the collection box enters a leaky gas exhaust pipe, where a cooling device cools it to room temperature. Finally, the flow rate is displayed by a flow meter. This solution accurately reflects the impact of thermal expansion caused by high temperatures during normal operation on the leakage amount. This device can be installed online, yielding relatively accurate results.

[0011] A preferred embodiment of the online flow test device for the leakage of the high-temperature and high-pressure valve of an aircraft is that the leaking gas collection box includes two splicing components. Each splicing component has a semi-hoop at each end. The semi-hoop includes a semi-cylindrical tube and two horizontal plates. The two horizontal plates are respectively connected to both sides of the semi-cylindrical tube. The two horizontal plates are on the same plane, which passes through the axis of the semi-cylindrical tube.

[0012] The online flow test device for the leakage of the aircraft's high-temperature and high-pressure valve also includes two port seals. Each port seal includes a circular sleeve and two planar fins. The two fins are integrally formed on both sides of the circular sleeve, and the two fins are on the same plane, which passes through the axis of the circular sleeve.

[0013] Both port seals are tightly fitted onto the air inlet pipe and the air outlet pipe respectively by the circular sleeves. The semi-hoops at both ends of each splice adhere to the same side of both port seals, including the semi-cylindrical tube adhering to the circular sleeve and the two horizontal plates adhering to the two fins. The semi-hoops at the same end of both splices clamp the same port seal, including each pair of opposite horizontal plates clamping one fin, and are sealed and locked by several bolts passing through the two horizontal plates and one fin.

[0014] By adopting the above technical solution, the two splicing parts can be easily disassembled and installed, and the two ends of the two splicing parts can be sealed together, forming a sealed connection with the air inlet pipe and the air outlet pipe to prevent air leakage.

[0015] A preferred embodiment of the online flow test device for the leakage of high-temperature and high-pressure valves on aircraft is that each of the splicing components is equipped with a set of cooling components. The cooling components include coils. The splicing components have a double-layer structure, and the coils are evenly distributed within the double-layer structure. The two sets of coils avoid the three ports of the leaking gas collection box.

[0016] By adopting the above technical solution, water can be circulated through the coil to cool the ambient gas inside the leaking gas collection box, simulating the working environment temperature of a high-temperature and high-pressure valve, thereby improving the accuracy of the test results.

[0017] A preferred embodiment of the online flow test device for the external leakage of high-temperature and high-pressure valves on aircraft includes two side seals. Each side seal is U-shaped. Each splice has a U-shaped side. Each side seal is fitted with a mat between the U-shaped sides of the two splices on the same side. The two ends of each side seal abut against two fins, and a high-temperature resistant adhesive is used to seal the connection between the side seal and the fins. The device is sealed and fixed by several bolts passing through the U-shaped sides of the two splices and the side seals.

[0018] By adopting the above technical solution, the U-shaped sides of the two splicing parts are also sealed to prevent air leakage.

[0019] A preferred embodiment of the online flow test device for the leakage of high-temperature and high-pressure valves on aircraft is that the leaking gas exhaust pipe has a spiral section. The cooling device is a cooling water tank. The spiral section is located within the cooling water tank. When the cooling water tank is full of water, it can submerge the spiral section. The cooling water tank is connected to an inlet pipe and a drain pipe.

[0020] By adopting the above technical solution and controlling the water flow rate in the cooling water tank, the temperature of the leaked gas in the spiral tube section can be controlled to a normal temperature, which can be 0~50℃.

[0021] Secondly, this application also proposes an online actual flow test method for the leakage of high temperature and high pressure valves in aircraft, and adopts the following technical solution.

[0022] An online actual flow test method for the leakage of high-temperature and high-pressure valves in aircraft is disclosed, which employs an online actual flow test device for the leakage of high-temperature and high-pressure valves in aircraft. The online actual flow test method for the leakage of high-temperature and high-pressure valves in aircraft includes the following stages.

[0023] Assembly Stage: Place the two port seals over the air inlet pipe and the air outlet pipe. Disconnect the connector from the high-temperature, high-pressure valve on the aircraft. Connect the air inlet pipe to the air inlet of the high-temperature, high-pressure valve online, and connect the air outlet pipe to the air outlet of the high-temperature, high-pressure valve. Wrap the two splice pieces around the high-temperature, high-pressure valve, with the valve located in the middle of the internal space of the two splice pieces. Align the half-hoops of the two splice pieces with the port seals. Fix the two ends of the two splice pieces to the two port seals respectively, and seal the U-shaped sides of the two splice pieces to achieve a relatively sealed connection. Install the ambient temperature sensor, the leaking gas exhaust pipe, the cooling device, the exhaust temperature sensor, and the flow meter. Introduce cooling water into each set of coils. Start the cooling device.

[0024] First test phase: Hot air at a temperature of 380℃~420℃ and a pressure of 164psi~223psi is introduced into the air inlet pipe. The ambient temperature sensor detects the temperature as T1. If T1 < 80℃, the cooling water flow rate of each coil is reduced until T1 is between 80℃ and 140℃. If T1 > 140℃, the cooling water flow rate of each coil is increased until T1 is between 80℃ and 140℃. The exhaust temperature sensor detects the temperature as T2. If T2 ≥ 50℃, the cooling device is adjusted until T2 < 50℃. When T1 is between 80℃ and 140℃ and T2 < 50℃, after the flow meter reading stabilizes, the stable flow rate reading of the flow meter is taken as the leakage of the high-temperature and high-pressure valve.

[0025] By adopting the above technical solution, this method allows for the online assembly of a testing device to test the leakage of high-temperature, high-pressure valves on the production line. Hot air at 380℃~420℃ and a pressure of 164psi~223psi simulates the air temperature and pressure during normal operation of the high-temperature, high-pressure valve (generally 20 minutes after engine startup). The resulting valve leakage is more consistent with actual conditions, and the test results are more accurate. This method also simulates the ambient temperature during normal operation of the high-temperature, high-pressure valve by introducing cooling water through coils, further enhancing the accuracy of the valve leakage test results. Finally, cooling the leaking gas to room temperature ensures accurate flow meter readings.

[0026] A preferred embodiment of the online actual flow test method for the leakage of high-temperature and high-pressure valves in aircraft includes a second test stage: hot air with a temperature of 480℃~520℃ and a pressure of 164psi~223psi is introduced into the air intake pipe. The ambient temperature sensor senses the temperature as T1. If T1 < 80℃, the cooling water flow rate of each coil is reduced until T1 is between 80℃ and 140℃. If T1 > 140℃, the cooling water flow rate of each coil is increased until T1 is between 80℃ and 140℃. The exhaust temperature sensor senses the temperature as T2. If T2 ≥ 50℃, the cooling device is adjusted until T2 < 50℃. When T1 is between 80℃ and 140℃ and T2 < 50℃, after the flow meter reading stabilizes, the flow meter reading is taken as the leakage of the high-temperature and high-pressure valve.

[0027] By adopting the above technical solution, when the engine compressor starts for 10 to 20 minutes, the air passing through the high-temperature and high-pressure valve reaches a temperature of 480°C to 520°C. Therefore, this solution also simulates the condition when the engine compressor starts for 10 to 20 minutes and tests the leakage of the high-temperature and high-pressure valve under this condition to determine whether the condition of the high-temperature and high-pressure valve is within the normal working range.

[0028] A preferred embodiment of the online actual flow test method for the leakage of the high temperature and high pressure valve of the aircraft is that, after the reading of the flow meter stabilizes, specifically, the difference between the highest and lowest values ​​of the flow meter reading within 30 seconds does not exceed 2L / min, and the stable flow reading is the last reading at the end of the 30 seconds.

[0029] By adopting the above technical solution, the flow meter readings have become stable and the readings are accurate.

[0030] A preferred embodiment of the online actual flow test method for the leakage of the high-temperature and high-pressure valve of an aircraft includes a third test stage after the assembly stage: hot air at a temperature of 600℃~650℃ and a pressure of 164psi~223psi is introduced into the air intake pipe. The ambient temperature sensor senses the temperature as T1. If T1 < 80℃, the cooling water flow rate of each group of coils is reduced until T1 is between 80℃ and 140℃. If T1 > 140℃, the cooling water flow rate of each group of coils is increased until T1 is between 80℃ and 140℃. The exhaust temperature sensor senses the temperature as T2. If T2 ≥ 50℃, the cooling device is adjusted until T2 < 50℃. When T1 is between 80℃ and 140℃ and T2 < 50℃, after the flow meter reading stabilizes, the flow meter reading is taken as the leakage of the high-temperature and high-pressure valve.

[0031] By adopting the above technical solution, when the engine compressor is first started, the temperature of the compressed gas is as high as 600℃~650℃. Therefore, hot air with a temperature of 600℃~650℃ and a pressure of 164psi~223psi is introduced into the air intake pipe. The leakage data of the high-temperature and high-pressure valve at this operating temperature can be obtained. The leakage data of the high-temperature and high-pressure valve at this temperature can be compared with the threshold to determine whether the high-temperature and high-pressure valve can work normally at this temperature.

[0032] An online flow test method for the external leakage of an aircraft high-temperature and high-pressure valve is disclosed, employing a cooling water tank with inlet and outlet pipes as the cooling device. The method includes: introducing hot air into the air inlet pipe; the exhaust temperature sensor detects a temperature T2; if T2 ≥ 50°C, the flow rate of the cooling water in the cooling water tank is increased to reduce T2 < 50°C.

[0033] By adopting the above technical solution, this device can effectively acquire and control the temperature of the leaked air before it passes through the flow meter, so as to collect the flow meter data at room temperature, making the results more accurate.

[0034] In summary, the online flow test device and method for the external leakage of high-temperature and high-pressure valves in this application have the following beneficial effects: This scheme allows for online assembly of the test device to test the external leakage of high-temperature and high-pressure valves online. The introduced air simulates the temperature and pressure of air passing through the high-temperature and high-pressure valve during engine compressor startup, 10-20 minutes of startup, and normal operation (after 20 minutes of startup). The valve leakage results measured using this type of airflow are more consistent with actual conditions, and the test results are more accurate. This scheme also simulates the ambient temperature where the high-temperature and high-pressure valve operates by introducing cooling water through coils, making the valve leakage test results more accurate. Finally, cooling the leaking gas to room temperature ensures accurate flow meter readings. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the connection structure of an online actual flow test device for the leakage of a high-temperature and high-pressure valve in an aircraft.

[0036] Figure 2 This is a schematic diagram showing the splicing of two port seals and two side seals.

[0037] Figure 3 for Figure 1 A schematic diagram of the AA section.

[0038] Figure 4 This is a schematic diagram of the splicing surface of the splicing components.

[0039] Reference numerals: 1. Air inlet pipe; 2. Leakage gas collection box; 3. Air outlet pipe; 4. Ambient temperature sensor; 5. Leakage gas exhaust pipe; 6. Cooling device; 7. Exhaust temperature sensor; 8. Flow meter; 9. Port seal; 10. Side seal; 21. Connecting piece; 901. Circular sleeve; 902. Fin; 211. Main body; 212. Semi-hoop; 2121. Semi-cylindrical tube; 2122. Horizontal plate; 2111. U-shaped side; 213. Coil. Detailed Implementation

[0040] The technical solutions in the embodiments 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 following embodiments, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0041] like Figure 1 An online real-flow testing device for the leakage of an aircraft high-temperature and high-pressure valve includes an air inlet pipe 1, a leaked gas collection box 2, an air outlet pipe 3, an ambient temperature sensor 4, a leaked gas exhaust pipe 5, a cooling device 6, an exhaust temperature sensor 7, and a flow meter 8. Figure 2 The online actual flow test device for the leakage of the high temperature and high pressure valve of the aircraft also includes two port seals 9 and two side seals 10.

[0042] like Figure 1 The leaking gas collection box 2 is assembled from two splicing parts 21 to form a cylindrical box body. The two ends of the box body are cylindrical heads, which are seamlessly connected to the air inlet pipe 1 and the air outlet pipe 3, respectively. The sides of the two splicing parts 21 are also seamlessly connected to each other. This seamless connection is assisted by two port seals 9 and two side seals 10.

[0043] like Figure 3 Each port seal 9 comprises a circular sleeve 901 and two planar fins 902. The two fins 902 are square and symmetrically connected to both sides of the circular sleeve 901, and the two fins 902 and the circular sleeve 901 are integrally formed. The two fins 902 are in the same plane, and this plane passes through the axis of the circular sleeve 901.

[0044] Each side seal 10 is a U-shaped sealing strip. The port seal 9 and the side seal 10 can be made of high-temperature resistant asbestos.

[0045] like Figure 1The structure of each splice 21 of the leaked gas collection box 2 is as follows: a semi-cylindrical sleeve is the main body 211, and both ends of the main body 211 are semi-enclosed by planar semi-circular plates perpendicular to the main body 211. A half-hoop 212 is vertically connected to each semi-circular plate. The half-hoop 212 is parallel to the main body 211. A semi-circular opening is left in the inner area semi-enclosed by the half-hoop 212. The diameter of the half-hoop 212 is approximately equal to the diameter of the air inlet pipe 1 and the air outlet pipe 3. This structure allows two splices 21 to be assembled into a cylindrical tube, with two cylindrical pipe joints formed by four half-hoops 212 at each end.

[0046] like Figure 4 In order to seamlessly abut with the port seal 9, one adaptation structure of the semi-circular plate 212 includes a semi-cylindrical tube 2121 and two square horizontal plates 2122. The two horizontal plates 2122 are integrally formed on both sides of the semi-cylindrical tube 2121. The two horizontal plates 2122 are on the same plane, and the plane passes through the axis of the semi-cylindrical tube 2121.

[0047] like Figure 4 At the seam of the splice 21, the main body 211 and the semi-circular piece are connected to form a U-shaped side 2111. The two splice 21 are sealed and connected by two port seals 9 and two U-shaped side seals 10, and locked together by bolts.

[0048] When installing the online flow testing device, for the high-temperature and high-pressure valve on the aircraft, the connecting components of the high-temperature and high-pressure valve can be disassembled first. Take one port seal 9 and insert it into the end of the air inlet pipe 1 a certain distance inward. Take another port seal 9 and insert it into the end of the air outlet pipe 3 a certain distance inward. Connect the air inlet pipe 1 to the air inlet of the high-temperature and high-pressure valve, and connect the air outlet pipe 3 to the air outlet of the high-temperature and high-pressure valve. Next, the two splicing parts 21 need to be spliced ​​together and wrapped around the high-temperature and high-pressure valve: first, take one splicing part 21 and half-fit it under the high-temperature and high-pressure valve. The half-hoops 212 at both ends of the splicing part 21 should respectively fit the lower surface of the two port seals 9. Specifically, at each end, the semi-cylindrical tube 2121 fits the lower half of the circular sleeve 901, and the two horizontal plates 2122 fit the lower surface of the two fins 902. Then, place the two U-shaped side seals 10 on the two U-shaped sides 2111 of the splicing part 21 that was placed first, such as... Figure 2The two ends of the two side seals 10 abut against the two fins 902, and each end of the side seal 10 and each fin 902 are connected with high-temperature resistant adhesive. Then, another splice 21 is half-fitted above the high-temperature and high-pressure valve. The half-hoops 212 at both ends of the splice 21 are respectively attached to the upper surfaces of the two port seals 9. Specifically, at each end, a semi-cylindrical tube 2121 is attached to the upper half of the circular sleeve 901, and two horizontal plates 2122 are attached to the upper surfaces of the two fins 902. The two U-shaped sides 2111 of the subsequent splicing component 21 are attached to the upper surfaces of the two U-shaped side seals 10; each horizontal plate 2122, fin 902, U-shaped side 2111 of splicing component 21 and U-shaped side seal 10 are provided with several through holes, and several bolts are passed through these through holes and locked, so that the two horizontal plates 2122 clamp a fin 902 and are sealed together, and the two U-shaped sides 2111 of splicing component 21 clamp the U-shaped side seal 10 and are sealed together.

[0049] like Figure 1 Each splice 21 has a double-layer stainless steel structure. A set of coils 213 is installed between the double-layer stainless steel of each splice 21. One end of the coil 213 is connected to the cooling water source, and the other end drains water outward. Water flows through the coil 213 to cool the air between the two splices 21, so as to simulate the working environment temperature of the high-temperature and high-pressure valve.

[0050] like Figure 1 The leak gas collection box 2, assembled from two splicing parts 21, has three openings, with the others sealed. The first opening is seamlessly connected to the air inlet pipe 1, the second to the air outlet pipe 3, and the third to the leak gas exhaust pipe 5. Two sets of coils 213 avoid these three openings. The ambient temperature sensor 4 is installed in the third opening, and its sensed temperature should be 80~140℃, simulating the working environment temperature of the high-temperature, high-pressure valve. If not, the temperature can be controlled by adjusting the water flow rate within the coils 213.

[0051] Currently, ambient temperature air is generally used to indicate leakage flow rate, therefore, the air, which is typically between 80 and 140°C, needs to be cooled to ambient temperature. The middle section of the leakage gas exhaust pipe 5 is a spiral tube segment. The cooling device 6 is a cooling water tank, within which the spiral tube segment is located, submerged by water. The cooling water tank is connected to an inlet pipe and an outlet pipe; adjusting the inlet water rate regulates the cooling temperature, ensuring the air temperature within the spiral tube segment reaches ambient temperature. To detect the cooled air temperature, an exhaust temperature sensor 7 is installed in the pipe segment following the spiral tube segment of the leakage gas exhaust pipe 5. A flow meter 8 is also installed after the exhaust temperature sensor 7 on the leakage gas exhaust pipe 5 to detect the flow rate of the cooled leakage gas. The leaked air is discharged into the atmosphere after passing through the flow meter 8.

[0052] The structure and assembly method of the online actual flow test device for the external leakage of high temperature and high pressure valves of aircraft have been introduced above. The following describes the online actual flow test method for the external leakage of high temperature and high pressure valves of aircraft, which is based on the online actual flow test device for the external leakage of high temperature and high pressure valves of aircraft.

[0053] The online flow test method for the external leakage of aircraft high-temperature and high-pressure valves includes an assembly stage, a first test stage, a second test stage, and a third test stage. The assembly stage is similar to the assembly method of the online flow test device for the external leakage of aircraft high-temperature and high-pressure valves described above. This stage includes assembling the components and then introducing cooling water into each group of coils 213, as well as circulating cooling water in the cooling water tank. The steps for the other three stages are as follows. It should be noted that the first, second, and third test stages can be performed in any order, not necessarily sequentially.

[0054] The first test phase involves introducing hot air at a temperature of 380℃~420℃ and a pressure of 164psi~223psi into the air intake pipe 1. Any value within this range is acceptable, as this is the ventilation temperature during normal operation of the high-temperature, high-pressure valve (20 minutes after the engine compressor starts). This scheme also controls the leakage during the ventilation test. The ambient temperature specified by the valve is 80℃~140℃, monitored by the ambient temperature sensor 4, whose sensing temperature is T1. If T1 < 80℃, the cooling water flow rate of each coil 213 is reduced until T1 is between 80℃ and 140℃; if T1 > 140℃, the cooling water flow rate of each coil 213 is increased until T1 is between 80℃ and 140℃. The final leakage test is based on the flow rate of ambient temperature air. Therefore, the leaking air in the leaking gas exhaust pipe 5 needs to be cooled to ambient temperature. The exhaust temperature sensor 7 is used to sense the temperature of the cooled leaking air and control it to be less than 50℃. The exhaust temperature sensor 7 senses the temperature T2. If T2 ≥ 50℃, the cooling water flow rate in the cooling water tank is increased until T2 < 50℃. After the above adjustments, when T1 is between 80℃ and 140℃ and T2 < 50℃, after the flow meter 8 reading stabilizes, the stable flow rate reading of the flow meter 8 is taken as the leakage of the high-temperature and high-pressure valve. Specifically, the difference between the highest and lowest values ​​of the flow meter 8 reading within 30 seconds should not exceed 2L / min, and the stable flow rate reading is the last reading at the end of those 30 seconds. This stabilization process generally takes 5 to 15 minutes. For aircraft high-temperature and high-pressure valves, the leakage rate tested in this stage should be less than 100L / min.

[0055] The second test phase involves introducing hot air at a temperature of 480℃~520℃ and a pressure of 164psi~223psi into the air intake pipe 1. This can be any temperature within this range. This phase simulates the airflow temperature and pressure of the high-temperature, high-pressure valve during the compressor startup process (10-20 minutes). The ambient temperature of the valve is controlled to be 80℃~140℃, monitored by the ambient temperature sensor 4, with a sensing temperature of T1. If T1 < 80℃, the cooling water flow rate of each coil 213 is reduced until T1 is between 80℃ and 140℃; if T1 > 140℃, the cooling water flow rate of each coil 213 is increased until T1 is between 80℃ and 140℃. Normal temperature air is used as the medium for the test flow rate. For exhaust air at 80℃~140℃, cooling is achieved through a cooling water tank. After cooling, the exhaust temperature sensor 7 detects the temperature as T2. If T2 ≥ 50℃, the cooling water flow rate in the tank is increased until T2 < 50℃. After these adjustments, when T1 is between 80℃ and 140℃ and T2 < 50℃, and the flow meter 8 reading stabilizes, the flow meter reading is taken as the leakage rate of the high-temperature, high-pressure valve. Specifically, the difference between the highest and lowest flow meter readings within 30 seconds should not exceed 2 L / min. The stable flow reading is the final reading at the end of those 30 seconds. This stabilization process typically takes 5~15 minutes. For aircraft high-temperature, high-pressure valves, the leakage rate tested in this stage should be less than 100 L / min.

[0056] The third testing phase: Hot air at a temperature of 600℃~650℃ and a pressure of 164psi~223psi is introduced into the air intake pipe 1. The high-temperature, high-pressure valve must not only have a low leakage rate during normal operation and during the first 10~20 minutes of compressor startup, but also a normal air leakage rate immediately upon compressor startup (within the first 10 minutes). The air produced by the compressor at startup is 600℃~650℃, and this produced air immediately passes through the high-temperature, high-pressure valve. During this phase, the ambient temperature of the valve is controlled to be 80℃~140℃, sensed by the ambient temperature sensor 4, with a sensed temperature of T1. If T1 < 80℃, the cooling water flow rate of each coil 213 is reduced until T1 is between 80℃ and 140℃; if T1 > 140℃, the cooling water flow rate of each coil 213 is increased until T1 is between 80℃ and 140℃. In this stage, flow rate testing is also conducted using ambient temperature air as the standard. Therefore, the exhaust air, ranging from 80℃ to 140℃, needs to be cooled. After cooling, the exhaust temperature sensor 7 senses the temperature as T2. If T2 ≥ 50℃, the cooling water flow rate in the cooling water tank is increased until T2 < 50℃. After the above adjustments, when T1 is between 80℃ and 140℃ and T2 < 50℃, and the reading of flow meter 8 stabilizes, the flow rate reading of flow meter 8 is taken as the leakage rate of the high-temperature, high-pressure valve. This stabilization is defined as the difference between the highest and lowest flow rate readings of flow meter 8 within 30 seconds not exceeding 2 L / min. The stable flow rate reading is the final reading at the end of those 30 seconds. This stabilization process typically takes 5–15 minutes. For aircraft high-temperature, high-pressure valves, the leakage rate tested in this stage should be less than 100 L / min.

[0057] This application's online flow test method for high-temperature, high-pressure valve leakage can accurately measure gas leaks within a temperature range of 380℃ to 650℃. This application is the first to propose the concept of online flow testing for high-temperature, high-pressure valve leakage in aircraft gas supply systems, making the production and maintenance of such valves more practical. This application uses cooling components to control the ambient temperature around the valve, realistically reproducing the valve's operating state and ensuring continuous and stable operation. This application employs a cooling device 6 to reduce the temperature of the leaking gas to room temperature, protecting the normal operation of the conventional flow meter 8 and improving measurement accuracy.

[0058] Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. 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 online actual flow test device for the leakage of high-temperature and high-pressure valves in aircraft, characterized in that, It includes an air inlet pipe (1), a leak gas collection box (2), an air outlet pipe (3), an ambient temperature sensor (4), a leak gas exhaust pipe (5), a cooling device (6), an exhaust temperature sensor (7), and a flow meter (8). The interior of the leak gas collection box (2) has space for installing high temperature and high pressure valves; the leak gas collection box (2) has three openings, and the other positions are closed. The first opening is seamlessly connected to the air inlet pipe (1), the second opening is seamlessly connected to the air outlet pipe (3), and the third opening is seamlessly connected to the leak gas exhaust pipe (5); the box wall of the leak gas collection box (2) is equipped with cooling components; The air inlet pipe (1) is inserted into the leaked gas collection box (2) to connect to the air inlet of the high temperature and high pressure valve; the air outlet pipe (3) is inserted into the leaked gas collection box (2) to connect to the air outlet of the high temperature and high pressure valve. The ambient temperature sensor (4) is installed in the third port; The cooling device (6) acts on a section of the leaking gas exhaust pipe (5); the exhaust temperature sensor (7) is installed in the section of the leaking gas exhaust pipe (5) after the cooling device (6); the flow meter (8) is installed on the section of the leaking gas exhaust pipe (5) after the exhaust temperature sensor (7).

2. The online actual flow test device for the leakage of high temperature and high pressure valves in aircraft according to claim 1, characterized in that, The leaked gas collection box (2) includes two splicing parts (21); each splicing part (21) has a half-hoop (212) at each end; the half-hoop (212) includes a semi-cylindrical tube (2121) and two horizontal plates (2122); the two horizontal plates (2122) are respectively connected to both sides of the semi-cylindrical tube (2121); the two horizontal plates (2122) are on the same plane, which passes through the axis of the semi-cylindrical tube (2121); The online actual flow test device for the leakage of the high temperature and high pressure valve of the aircraft also includes two port seals (9); each of the port seals (9) includes a circular sleeve (901) and two planar fins (902); the two fins (902) are integrally formed on both sides of the circular sleeve (901), and the two fins (902) are on the same plane, which passes through the axis of the circular sleeve (901); Both of the port seals (9) are tightly fitted onto the air inlet pipe (1) and the air outlet pipe (3) respectively by the circular sleeve (901); the half-hoops (212) at both ends of each splice (21) are attached to the same side of the two port seals (9), including the semi-cylindrical tube (2121) attached to the circular sleeve (901), and the two horizontal plates (2122) attached to the two fins (902); the half-hoops (212) at the same end of the two splices (21) clamp the same port seal (9), including each pair of opposite horizontal plates (2122) clamping one fin (902), and sealed and locked by several bolts passing through the two horizontal plates (2122) and one fin (902).

3. The online actual flow test device for the leakage of high temperature and high pressure valves in aircraft according to claim 2, characterized in that, Each of the splicing components (21) is equipped with a set of cooling components; the cooling components include coils (213); the splicing component (21) has a double-layer structure, and the coils (213) are evenly distributed in the double-layer structure; the two sets of coils (213) avoid the three ports of the leaking gas collection box (2).

4. The online actual flow test device for the leakage of high temperature and high pressure valves in aircraft according to claim 3, characterized in that, The online actual flow test device for the leakage of the high temperature and high pressure valve of the aircraft also includes two side seals (10); the side seals (10) are U-shaped; each splice (21) has a U-shaped side (2111); each side seal (10) is adapted to the ground mat between the U-shaped side (2111) on the same side of the two splices (21); the two ends of the side seals (10) are connected to the two fins (902), and the side seals (10) and the fins (902) are sealed and connected by high temperature resistant adhesive; and sealed and fixed by several bolts passing through the U-shaped side (2111) of the two splices (21) and the side seals (10).

5. The online actual flow test device for the leakage of high temperature and high pressure valves in aircraft according to claim 3, characterized in that, The leaking gas exhaust pipe (5) has a spiral pipe section; the cooling device (6) is a cooling water tank; the spiral pipe section is located in the cooling water tank; the cooling water tank can submerge the spiral pipe section when it is full of water; the cooling water tank is connected to an inlet pipe and a drain pipe.

6. A method for online actual flow testing of leakage from high-temperature and high-pressure valves in aircraft, characterized in that, The online actual flow test device for the leakage of high-temperature and high-pressure valves of aircraft, as described in claim 3 or 4, is used for testing; the online actual flow test method for the leakage of high-temperature and high-pressure valves of aircraft includes: Assembly stage: Place the two port seals (9) over the air inlet pipe (1) and the air outlet pipe (3); remove the connector from the high-temperature and high-pressure valve on the aircraft; connect the air inlet pipe (1) to the air inlet of the high-temperature and high-pressure valve online, and connect the air outlet pipe (3) to the air outlet of the high-temperature and high-pressure valve; wrap the two splicing pieces (21) around the high-temperature and high-pressure valve, with the high-temperature and high-pressure valve located in the middle of the internal space of the two splicing pieces (21), and align the half-hoops (212) of the two splicing pieces (21). The port seal (9) fixes the two ends of the two splicing parts (21) to each other and seals the U-shaped sides (2111) of the two splicing parts (21) so that the two splicing parts (21) are relatively sealed and connected; install the ambient temperature sensor (4), the leaking gas exhaust pipe (5), the cooling device (6), the exhaust temperature sensor (7) and the flow meter (8); introduce cooling water into each set of coils (213); start the cooling device (6); First test phase: Hot air with a temperature of 380℃~420℃ and an air pressure of 164psi~223psi is introduced into the air inlet pipe (1). The ambient temperature sensor (4) senses the temperature as T1. If T1 < 80℃, the cooling water flow rate of each group of coils (213) is reduced until T1 is between 80℃ and 140℃. If T1 > 140℃, the cooling water flow rate of each group of coils (213) is increased until T1 is between 80℃ and 140℃. The exhaust temperature sensor (7) senses the temperature as T2. If T2 ≥ 50℃, the cooling device (6) is adjusted until T2 < 50℃. When T1 is between 80℃ and 140℃ and T2 < 50℃, after the reading of the flow meter (8) stabilizes, the stable flow reading of the flow meter (8) is read as the leakage of the high temperature and high pressure valve.

7. The online actual flow test method for the leakage of high-temperature and high-pressure valves in aircraft according to claim 6, characterized in that, The online actual flow test method for the leakage of the high temperature and high pressure valve of the aircraft also includes a second test stage: hot air with a temperature of 480℃~520℃ and an air pressure of 164psi~223psi is introduced into the air intake pipe (1). The ambient temperature sensor (4) senses the temperature as T1. If T1 < 80℃, the cooling water flow rate of each group of coils (213) is reduced until T1 is between 80℃ and 140℃. If T1 > 140℃, the cooling water flow rate of each group of coils (213) is increased until T1 is between 80℃ and 140℃. The exhaust temperature sensor (7) senses the temperature as T2. If T2 ≥ 50℃, the cooling device (6) is adjusted until T2 < 50℃. When T1 is between 80℃ and 140℃ and T2 < 50℃, after the reading of the flow meter (8) stabilizes, the flow reading of the flow meter (8) is read as the leakage of the high temperature and high pressure valve.

8. The online actual flow test method for the leakage of high-temperature and high-pressure valves in aircraft according to claim 6 or 7, characterized in that, After the reading of the flow meter (8) stabilizes, specifically, the difference between the highest and lowest values ​​of the flow meter (8) within 30 seconds does not exceed 2L / min, and the stable flow reading is the last reading at the end of the 30 seconds.

9. The online actual flow test method for the leakage of high-temperature and high-pressure valves in aircraft according to claim 7, characterized in that, The online actual flow test method for the leakage of the high temperature and high pressure valve of the aircraft also includes a third test stage after the assembly stage: hot air with a temperature of 600℃~650℃ and an air pressure of 164psi~223psi is introduced into the air intake pipe (1). The ambient temperature sensor (4) senses the temperature as T1. If T1<80℃, the cooling water flow rate of each group of coils (213) is reduced until T1 is between 80℃ and 140℃. If T1>140℃, the cooling water flow rate of each group of coils (213) is increased until T1 is between 80℃ and 140℃. The exhaust temperature sensor (7) senses the temperature as T2. If T2≥50℃, the cooling device (6) is adjusted until T2<50℃. When T1 is between 80℃ and 140℃ and T2<50℃, after the reading of the flow meter (8) stabilizes, the flow reading of the flow meter (8) is read as the leakage of the high temperature and high pressure valve.

10. A method for online actual flow testing of the leakage of an aircraft high-temperature and high-pressure valve, characterized in that, The test is performed using the online actual flow test device for the leakage of the aircraft high temperature and high pressure valve as described in claim 5; the online actual flow test method for the leakage of the aircraft high temperature and high pressure valve includes: introducing hot air into the air intake pipe (1), the exhaust temperature sensor (7) sensing the temperature as T2, if T2≥50℃, then accelerating the cooling water flow rate of the cooling water tank so that T2<50℃.

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