Online real flow testing device and method for leakage amount of high-temperature and high-pressure valve of airplane

Abstract

The invention relates to the technical field of aircraft valve leakage amount testing, and particularly discloses an online real flow testing method for the leakage amount of an aircraft high-temperature and high-pressure valve. The online real flow testing device for the leakage amount of the high-temperature and high-pressure valve of the airplane comprises an air inlet pipe, a leakage gas collecting tank, an air outlet pipe, an environment temperature sensor, a leakage 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 leakage gas collecting tank and connected with the air inlet pipe and the air outlet pipe, hot air at various temperatures is introduced from the air inlet pipe when the high-temperature and high-pressure valve works, and the temperature of the environment where the high-temperature and high-pressure valve works is controlled by a cooling piece on the tank wall of the leakage gas collecting tank. Leakage gas enters the leakage gas exhaust pipe, the cooling device cools the leakage gas to the normal temperature, and the flow meter displays the flow of the leakage gas. According to the scheme, the influence of high-temperature and high-pressure air generated in the whole starting process of the engine on the leakage amount of the valve can be truly reflected.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft valve leakage testing, and in particular to an online real-flow testing device and method for aircraft high-temperature and high-pressure valve leakage testing. Background Art

[0002] The high-pressure bleed valve, pressure regulating / shut-off valve, and precooler regulating valve of the aircraft air source system are the key and important parts of the aircraft environmental control system. They work in the high-temperature vibration environment of the aircraft engine compartment and have a high failure rate. Such valves are electromagnetically controlled and pneumatically operated, with large size and complex structure. There are many valve function exhaust ports and inherent leakage points. If the leakage exceeds the standard, it will affect the system performance at the least, and in serious cases, it will cause the temperature of the surrounding structure to rise, posing a threat to flight safety. When producing or repairing aircraft accessories, the leakage of high-temperature and high-pressure valves is a must-check item, but it is generally tested with normal temperature gas, which cannot more truly reflect the impact of thermal expansion caused by high temperature on the leakage during normal operation. Summary of the invention

[0003] In view of the fact that the leakage of the high-temperature and high-pressure valve is detected by using normal temperature gas, which cannot truly reflect the impact of thermal expansion caused by high temperature on the leakage during normal operation, the present application proposes the following improvement plan.

[0004] In a first aspect, the present application proposes an online real-flow test device for the leakage of an aircraft high-temperature and high-pressure valve, and adopts the following technical solution.

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

[0006] The leaking gas collecting box has a space for installing a high-temperature and high-pressure valve. The leaking gas collecting box has three openings, and the other positions are closed. The first opening is seamlessly connected to the air inlet pipe, the second opening is seamlessly connected to the air outlet pipe, and the third opening is seamlessly connected to the leaking gas exhaust pipe. A cooling member is installed on the box wall of the leaking gas collecting box.

[0007] The air inlet pipe is inserted into the leakage gas collecting box to connect the air inlet of the high temperature and high pressure valve. The air outlet pipe is inserted into the leakage gas collecting box to connect the air outlet of the high temperature and 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 after the cooling device. The flow meter is installed on the section of the leaking gas exhaust pipe after the exhaust temperature sensor.

[0010] By adopting the above technical scheme, the high-temperature and high-pressure valve can be installed in the leakage gas collecting box, and the high-temperature and high-pressure valve is connected with an air inlet pipe and an air outlet pipe. Hot air simulating the normal ventilation temperature of the high-temperature and high-pressure valve is introduced from the air inlet pipe. The leakage gas collecting box can collect the gas leaked by the high-temperature and high-pressure valve. The leakage gas collecting box also uses the cooling parts on the box wall to control the ambient temperature of the high-temperature and high-pressure valve. The ambient temperature simulates the ambient temperature of the high-temperature and high-pressure valve when it is working. The leakage gas discharged from the leakage gas collecting box enters the leakage gas exhaust pipe, and the cooling device cools the leakage gas to normal temperature. Finally, the flow rate of the leakage gas is displayed by the flow meter. This scheme can more realistically reflect the impact of thermal expansion caused by high temperature on the leakage amount during normal operation. This device can be installed online to obtain more accurate results.

[0011] A preferred solution of the online real flow test device for the leakage of the aircraft high temperature and high pressure valve is that the leakage gas collecting box includes two splicing parts. Each of the two ends of the splicing part has a half hoop piece. The half hoop piece includes a semi-cylindrical tube and two transverse plates. The two transverse plates are respectively connected to the two sides of the semi-cylindrical tube. The two transverse plates are on the same plane, and the plane passes through the axis of the semi-cylindrical tube.

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

[0013] The two port seals are respectively tightly sleeved on the air inlet pipe and the air outlet pipe with the circular sleeve. The half-hoop pieces at both ends of each splicing piece fit the same side of the two port seals, including the semi-cylindrical tube fitting the circular sleeve, and the two transverse plates fitting the two fins. The half-hoop pieces at the same end of the two splicing pieces clamp the same port seal, including each of the two opposite transverse plates clamping one fin, and a plurality of bolts pass through the two transverse plates and one fin to seal and lock.

[0014] By adopting the above technical solution, the two splicing pieces can be easily disassembled and assembled, and the two ends of the two splicing pieces can be sealed and connected, and form a sealed connection with the air inlet pipe and the air outlet pipe to prevent air leakage.

[0015] A preferred solution of the online real flow test device for the leakage of the aircraft high temperature and high pressure valve is that each of the splicing parts is equipped with a group of the cooling parts. The cooling parts include coils. The splicing part has a double-layer structure, and the coils are evenly arranged in the double-layer structure. The two groups of coils avoid the three ports of the leakage gas collecting box.

[0016] By adopting the above technical solution, water can flow through the coil to cool the ambient gas inside the leaking gas collecting box, simulate the working environment temperature of the high-temperature and high-pressure valve, and improve the accuracy of the test results.

[0017] A preferred solution of the online real-flow test device for the leakage of the high-temperature and high-pressure valve of the aircraft is that the online real-flow test device for the leakage of the high-temperature and high-pressure valve of the aircraft also includes two side seals. The side seal is U-shaped. Each of the splicing pieces has a U-shaped side. Each of the side seals is adaptively placed between the U-shaped sides on the same side of the two splicing pieces. The two ends of the side seal are butt-jointed with the two fins, and the side seal and the fin are sealed and connected using high-temperature resistant glue. A plurality of bolts are passed through the U-shaped sides of the two splicing pieces and the side seals to seal and fix them.

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

[0019] A preferred solution of the online real-flow test device for the leakage of the aircraft high-temperature and high-pressure valve is that the leaking gas exhaust pipe has a spiral pipe section. The cooling device is a cooling water tank. The spiral pipe section is located in the cooling water tank. When the cooling water tank is filled with water, the spiral pipe section can be submerged. The cooling water tank is connected to a water inlet pipe and a drain pipe.

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

[0021] On the second aspect, the present application also proposes an online real-flow test method for the leakage of an aircraft high-temperature and high-pressure valve, and adopts the following technical solution.

[0022] An online real-flow test method for the leakage of a high-temperature and high-pressure valve of an aircraft is provided, and an online real-flow test device for the leakage of a high-temperature and high-pressure valve of an aircraft is used for testing. The online real-flow test method for the leakage of a high-temperature and high-pressure valve of an aircraft includes the following stages.

[0023] Assembly stage: Put the two port seals on the outside of the air inlet pipe and the air outlet pipe. Remove the connector of the high-temperature and high-pressure valve on the aircraft, connect the air inlet pipe to the air inlet of the high-temperature and high-pressure valve online, and connect the air outlet pipe to the air outlet of the high-temperature and high-pressure valve. Wrap the two splicing parts outside the high-temperature and high-pressure valve, and the high-temperature and high-pressure valve is located in the middle of the internal space of the two splicing parts that are connected. Align the half hoop pieces of the two splicing parts with the port seals, fix the two ends of the two splicing parts to each other respectively, and seal the U-shaped sides of the two splicing parts so that the two splicing parts are relatively sealed and connected. Install the ambient temperature sensor, the leaking gas exhaust pipe, the cooling device, the exhaust temperature sensor and the flow meter. Pass cooling water into each group of the coils respectively. Start the cooling device.

[0024] The 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. The ambient temperature sensor senses the temperature T1. If T1<80℃, the cooling water flow rate of each group of the coils is reduced until T1 is between 80℃~140℃. If T1>140℃, the cooling water flow rate of each group of the coils is increased until T1 is between 80℃~140℃. The exhaust temperature sensor senses the temperature T2. If T2≥50℃, the cooling device is adjusted until T2<50℃. When T1 is between 80℃~140℃ and T2<50℃, wait until the reading of the flowmeter is stable, and read the stable flow reading of the flowmeter as the leakage of the high-temperature and high-pressure valve.

[0025] By adopting the above technical solution, this solution can assemble the test device online to test the leakage of the high-temperature and high-pressure valve on the line. The hot air at 380℃~420℃ and the air pressure of 164psi~223psi simulates the air temperature and air pressure of the high-temperature and high-pressure valve during normal operation (generally 20 minutes after the engine is started). The valve leakage results measured based on this are more in line with the actual situation, and the test results are more accurate. This solution also simulates the ambient temperature of the high-temperature and high-pressure valve in normal operation by setting up coils to pass cooling water separately, so that the valve leakage test results are more accurate. Finally, the leaking gas is cooled to room temperature to make the flow meter reading accurate.

[0026] A preferred solution of the online real-flow test method for the leakage of the high-temperature and high-pressure valve of the aircraft is that the online real-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°C to 520°C and an air pressure of 164psi to 223psi is introduced into the air intake pipe, and the ambient temperature sensor senses a temperature of T1. If T1<80°C, the cooling water flow rate of each group of the coils is reduced until T1 is between 80°C and 140°C. If T1>140°C, the cooling water flow rate of each group of the coils is increased until T1 is between 80°C and 140°C. The exhaust temperature sensor senses a temperature of T2. If T2≥50°C, the cooling device is adjusted until T2<50°C. When T1 is between 80°C and 140°C and T2<50°C, after the reading of the flowmeter is stable, the flow reading of the flowmeter is read as the leakage of the high-temperature and high-pressure valve.

[0027] By adopting the above technical scheme, when the engine compressor is started for 10min to 20min, the air passing through the high-temperature and high-pressure valve is as high as 480℃~520℃. Therefore, this scheme also simulates the condition of the engine compressor when it is started for 10min to 20min, and tests the leakage of the high-temperature and high-pressure valve under this condition to determine whether the state of the high-temperature and high-pressure valve is within the normal working range.

[0028] A preferred solution for the online real-flow test method for the leakage of the aircraft high-temperature and high-pressure valve is that after the reading of the flow meter is stable, specifically, the difference between the highest and lowest flow readings of the flow meter 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 reading is stabilized and the reading result is accurate.

[0030] A preferred solution of the online real-flow test method for the leakage of the high-temperature and high-pressure valve of the aircraft is that the online real-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°C to 650°C and an air pressure of 164psi to 223psi is introduced into the air intake pipe, and the ambient temperature sensor senses a temperature of T1. If T1<80°C, the cooling water flow rate of each group of the coils is reduced until T1 is between 80°C and 140°C. If T1>140°C, the cooling water flow rate of each group of the coils is increased until T1 is between 80°C and 140°C. The exhaust temperature sensor senses a temperature of T2. If T2≥50°C, the cooling device is adjusted until T2<50°C. When T1 is between 80°C and 140°C and T2<50°C, after the reading of the flowmeter is stable, the flow reading of the flowmeter is read as the leakage of the high-temperature and high-pressure valve.

[0031] By adopting the above technical solution, when the engine compressor is just started, the temperature of the compressed gas is as high as 600℃~650℃, so it is set to introduce hot air with a temperature of 600℃~650℃ and an air pressure of 164psi~223psi into the air inlet pipe, and the leakage data of the high-temperature and high-pressure valve at the operating temperature is obtained. The leakage data of the high-temperature and high-pressure valve under this temperature state can be obtained, and compared with the threshold value, it is determined whether the high-temperature and high-pressure valve can work normally under this temperature state.

[0032] An online real-flow test method for the leakage of an aircraft high-temperature and high-pressure valve is used to test the leakage of an aircraft high-temperature and high-pressure valve using a cooling water tank with an inlet pipe and a drain pipe as a cooling device. The online real-flow test method for the leakage of an aircraft high-temperature and high-pressure valve comprises: introducing hot air into the air inlet pipe, the exhaust temperature sensor senses a temperature of T2, and if T2 ≥ 50°C, then accelerating the cooling water flow rate of the cooling water tank so that T2 < 50°C.

[0033] By adopting the above technical solution, the device can effectively obtain and control the temperature of the leaked air before passing through the flow meter, so as to reach a normal temperature state and then collect the flow meter data, making the result more accurate.

[0034] In summary, the online real-flow test device and method for the leakage of aircraft high-temperature and high-pressure valves of the present application have the following beneficial effects: the present solution can assemble the test device online to test the leakage of the high-temperature and high-pressure valves on the line. The introduced air simulates the condition of the air of corresponding temperature and pressure generated by the engine compressor when it is just started, 10 to 20 minutes after starting, and during normal operation (20 minutes after starting) passing through the high-temperature and high-pressure valve. The valve leakage results measured by the circulating air in this state are more in line with the actual situation, and the test results are more accurate. The present solution also simulates the ambient temperature of the high-temperature and high-pressure valve by setting up coils to introduce cooling water separately, so as to make the valve leakage test results more accurate. Finally, the leaking gas is cooled to room temperature to make the flow meter reading accurate. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0036] Figure 2 Schematic diagram of the splicing of two port seals and two side seals.

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

[0038] Figure 4 Schematic diagram of the joint surface of the joint parts.

[0039] Figure numerals: 1. air inlet pipe; 2. leaking gas collecting box; 3. air outlet pipe; 4. ambient temperature sensor; 5. leaking gas exhaust pipe; 6. cooling device; 7. exhaust temperature sensor; 8. flow meter; 9. port seal; 10. side seal; 21. splicing part; 901. round sleeve; 902. fin; 211. main body; 212. half hoop; 2121. semi-cylindrical tube; 2122. cross plate; 2111. U-shaped side; 213. coil. DETAILED DESCRIPTION

[0040] The technical solutions in the embodiments will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the following embodiments, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

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

[0042] like Figure 1 The leaking gas collecting box 2 is formed by splicing two splicing pieces 21 to form a cylindrical box body, and 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, and the sides of the two splicing pieces 21 are also seamlessly connected to each other. The seamless connection is assisted by two port seals 9 and two side seals 10.

[0043] like Figure 3 Each port seal 9 has a structure including 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. The two fins 902 and the circular sleeve 901 are integrally formed. The two fins 902 are in the same plane, and the plane passes through the axis of the circular sleeve 901.

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

[0045] like Figure 1The structure of each splicing piece 21 of the leaking gas collecting box 2 is that a semi-cylindrical sleeve is used as the main body 211, and the two ends of the main body 211 are semi-enclosed by a flat semicircular piece perpendicular to the main body 211, and each semicircular piece is vertically connected to a half hoop piece 212. The half hoop piece 212 is parallel to the main body 211. The semicircular piece leaves a semicircular opening in the inner area half-enclosed by the half hoop piece 212. The diameter of the half hoop piece 212 is substantially equal to the diameter of the air inlet pipe 1 and the air outlet pipe 3. The above structure allows the two splicing pieces 21 to be assembled into a cylindrical tube, with two cylindrical pipe joints at both ends being assembled by four half hoop pieces 212.

[0046] like Figure 4 In order to seamlessly abut with the port seal 9, an adaptation structure of the half hoop 212 includes a semi-cylindrical tube 2121 and two square cross plates 2122. The two cross plates 2122 are integrally formed on both sides of the semi-cylindrical tube 2121. The two cross 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 joint position of the splicing piece 21, the main body 211 and the semicircular piece are connected to form a U-shaped side 2111. The two splicing pieces 21 are sealed and connected by two port seals 9 and two U-shaped side seals 10, and are serially locked by bolts.

[0048] When installing the online real flow test device, for the high-temperature and high-pressure valve on the aircraft, you can first disassemble the components connected to the high-temperature and high-pressure valve, take one port seal 9 and insert it into the end of the air inlet pipe 1 for a distance inward, and take the other port seal 9 and insert it into the end of the air outlet pipe 3 for a 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. Then, the two splicing pieces 21 should be assembled and wrapped outside the high-temperature and high-pressure valve: first take a splicing piece 21 and half-sleeve it under the high-temperature and high-pressure valve, and the half hoop pieces 212 at both ends of the splicing piece 21 are respectively attached to the lower surfaces of the two port seals 9, specifically, at each end, the semi-cylindrical tube 2121 is attached to the lower half of the circular sleeve 901, and the two horizontal plates 2122 are attached to the lower surfaces of the two fins 902; then place the two U-shaped side seals 10 on the two U-shaped side edges 2111 of the splicing piece 21 that was placed first, such as Figure 2, the 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 by applying high temperature resistant glue; then take another splicing piece 21 half sleeve on the top of the high temperature and high pressure valve, and the half hoop pieces 212 at both ends of the splicing piece 21 are respectively attached to the upper surfaces of the two port seals 9, specifically, at each end, the semi-cylindrical tube 2121 is attached to the upper half of the circular sleeve 901, and the two horizontal plates 2122 are attached to the upper surfaces of the two fins 902 ; The two U-shaped sides 2111 of the rear-mounted splicing piece 21 fit the upper surfaces of the two U-shaped side seals 10; each cross plate 2122, the fin 902, the U-shaped side 2111 of the splicing piece 21 and the U-shaped side seal 10 are provided with a plurality of through holes, and a plurality of bolts are passed through these through holes and locked, so that the two cross plates 2122 clamp a fin 902 and are sealed and connected, and the U-shaped sides 2111 of the two splicing pieces 21 clamp the U-shaped side seals 10 and are sealed and connected.

[0049] like Figure 1 The main body 211 of each splicing piece 21 is a double-layer stainless steel structure. A group of coils 213 are installed between the double-layer stainless steel of each splicing piece 21. One end of the coil 213 is connected to the cooling water source, and the other end is drained outward. Water flows through the coil 213 to cool the air between the two splicing pieces 21 to simulate the working environment temperature of the high-temperature and high-pressure valve.

[0050] like Figure 1 The leaking gas collecting box 2 composed of two splicing pieces 21 has three openings, and the other positions are closed. The first opening has been seamlessly connected to the air inlet pipe 1, the second opening has been seamlessly connected to the air outlet pipe 3, and the third opening is used to seamlessly connect the leaking gas exhaust pipe 5. The two groups of coils 213 avoid these three openings. The ambient temperature sensor 4 is installed in the third opening, and the temperature it senses should be 80~140℃, that is, the working environment temperature of the simulated high temperature and high pressure valve. If not, the temperature can be controlled by adjusting the water flow rate in the coil 213.

[0051] At present, normal temperature air is generally used to indicate the leakage flow, so it is also necessary to cool the air at 80~140°C to normal temperature. The middle of the leakage gas exhaust pipe 5 is a spiral pipe section. The cooling device 6 is a cooling water tank, and the spiral pipe section is located in the cooling water tank. The cooling water tank is filled with water to submerge the spiral pipe section. The cooling water tank is connected to a water inlet pipe and a water outlet pipe. The cooling temperature can be adjusted by regulating the water inlet speed so that the air temperature in the spiral pipe section reaches a normal temperature state. In order to detect the temperature of the air after cooling, an exhaust temperature sensor 7 is also installed in the pipe section after the spiral pipe section of the leakage gas exhaust pipe 5. After the exhaust temperature sensor 7, the leakage gas exhaust pipe 5 is also equipped with a flow meter 8 to detect the leakage gas flow after cooling. The leaked air passes through the flow meter 8 and is discharged into the atmosphere.

[0052] The above introduces the structure and assembly method of the online real flow test device for the leakage of aircraft high-temperature and high-pressure valves. The following introduces the online real flow test method for the leakage of aircraft high-temperature and high-pressure valves. The method is completed based on the online real flow test device for the leakage of aircraft high-temperature and high-pressure valves.

[0053] The online real-flow test method for the leakage of aircraft high-temperature and high-pressure valves includes an assembly stage, a first test stage, a second test stage, a third test stage, and the like. The assembly stage is the same as the assembly method of the above-mentioned online real-flow test device for the leakage of aircraft high-temperature and high-pressure valves. The assembly stage includes respectively introducing cooling water into each group of the coils 213 after assembling the various components, and circulating cooling water in the cooling water tank. The following are the steps of the other three stages. It should be noted that the first test stage, the second test stage, and the third test stage can be arranged in any order, and do not have to be performed in sequence.

[0054] The 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, which can be any value in this range. This is the ventilation temperature when the high-temperature and high-pressure valve is working normally (20 minutes after the engine compressor is started). This scheme also controls the leakage process of the ventilation test. The ambient temperature of the valve is 80℃~140℃. The temperature is monitored by the ambient temperature sensor 4, and its sensing temperature is T1. If T1<80℃, the cooling water flow rate of each group of coils 213 is reduced until T1 is between 80℃~140℃; if T1>140℃, the cooling water flow rate of each group of coils 213 is increased until T1 is between 80℃~140℃; the test leakage is ultimately based on the flow rate of normal temperature air, so it is necessary to cool the leaking air in the leaking gas exhaust pipe 5 to normal temperature, and use the exhaust temperature sensor 7 to sense the temperature of the cooled leaking air to control it to be less than 50℃. The exhaust temperature sensor 7 senses a temperature of T2. If T2 ≥ 50°C, the cooling water flow rate of the cooling water tank is increased until T2 < 50°C. After the above adjustments, when T1 is between 80°C and 140°C and T2 < 50°C, 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. Specifically, the difference between the highest and lowest values ​​of the flow reading 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. The stabilization process generally takes 5 to 15 minutes. For aircraft high-temperature and high-pressure valves, the leakage tested in this stage should be less than 100L / min.

[0055] The second test phase: hot air with a temperature of 480℃~520℃ and an air pressure of 164psi~223psi is introduced into the air inlet pipe 1. The hot air can be any value in this range. This phase simulates the ventilation temperature and air pressure of the high-temperature and high-pressure valve when the engine compressor is started for 10min~20min. In this phase, the valve ambient temperature is also controlled to be 80℃~140℃, and it is monitored by the ambient temperature sensor 4, whose sensing temperature is T1. If T1<80℃, the cooling water flow rate of each group of coils 213 is reduced until T1 is between 80℃~140℃; if T1>140℃, the cooling water flow rate of each group of coils 213 is increased until T1 is between 80℃~140℃. Normal temperature air is also used as the medium for testing flow. For the air discharged at 80℃~140℃, it is cooled by the cooling water tank. After cooling, the temperature sensed by the exhaust temperature sensor 7 is T2. If T2≥50℃, the cooling water flow rate of the cooling water tank is accelerated until T2<50℃. After the above adjustment, when T1 is between 80℃~140℃ and T2<50℃, after the reading of the flow meter 8 is stable, the flow reading of the flow meter 8 is read as the leakage of the high-temperature and high-pressure valve. Specifically, the difference between the highest and lowest values ​​of the flow reading 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. The stabilization process is generally 5~15min. For the aircraft high-temperature and high-pressure valve, the leakage tested in this stage should be less than 100L / min.

[0056] The third test phase: hot air with a temperature of 600℃~650℃ and an air pressure of 164psi~223psi is introduced into the air inlet pipe 1. The high temperature and high pressure valve should not only have a low leakage during normal working process and 10min~20min when the engine compressor starts, but also have a normal air leakage when the engine compressor is just started (within 10 minutes of starting). The air temperature produced when the engine compressor is just started is 600℃~650℃, and the produced air immediately passes through the high temperature and high pressure valve. In this stage, the ambient temperature of the valve is also controlled to be 80℃~140℃, which is sensed by the ambient temperature sensor 4, and its sensing temperature is T1. If T1<80℃, the cooling water flow rate of each group of coils 213 is reduced until T1 is between 80℃~140℃; if T1>140℃, the cooling water flow rate of each group of coils 213 is increased until T1 is between 80℃~140℃. In this stage, the flow test is also carried out with normal temperature air as the standard, so the air discharged at 80℃~140℃ needs to be cooled. After cooling, the temperature sensed by the exhaust temperature sensor 7 is T2. If T2≥50℃, the cooling water flow rate of the cooling water tank is accelerated until T2<50℃. After the above adjustment, when T1 is between 80℃~140℃ and T2<50℃, after the reading of the flow meter 8 is stable, the flow reading of the flow meter 8 is the leakage of the high temperature and high pressure valve. The reading is stable, specifically, the difference between the highest and lowest values ​​of the flow reading 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. The stabilization process is generally 5~15min. For the high temperature and high pressure valve of the aircraft, the leakage tested in this stage should be less than 100L / min.

[0057] The online real-flow test method for the leakage of high-temperature and high-pressure valves of the present application can accurately measure gas leakage in the temperature range of 380°C to 650°C. The present application proposes for the first time the concept of online real-flow testing of the leakage of high-temperature and high-pressure valves in aircraft air source systems, making the production and maintenance of such valves more practical. The present application uses a cooling part to control the ambient temperature around the valve, truly reproduces the working state of the valve, and ensures that the valve can work continuously and stably. The present application uses a cooling device 6 to reduce the temperature of the leaking gas to room temperature, protects the normal use of the conventional flow meter 8, and improves the measurement accuracy.

[0058] Although the present application has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. An online real-flow test device for the leakage of aircraft high-temperature and high-pressure valves, characterized in that: It comprises an air inlet pipe (1), a leaking gas collecting box (2), an air outlet pipe (3), an ambient temperature sensor (4), a leaking gas exhaust pipe (5), a cooling device (6), an exhaust temperature sensor (7) and a flow meter (8); The leaking gas collecting box (2) has a space inside for installing a high-temperature and high-pressure valve; the leaking gas collecting 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 leaking gas exhaust pipe (5); a cooling element is installed on the box wall of the leaking gas collecting box (2); The air inlet pipe (1) is inserted into the leakage gas collecting box (2) to be connected to the air inlet of the high-temperature and high-pressure valve; the air outlet pipe (3) is inserted into the leakage gas collecting box (2) to be connected to the air outlet of the high-temperature and high-pressure valve; The ambient temperature sensor (4) is installed in the third opening; 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) located after the cooling device (6); and the flow meter (8) is installed on the section of the leaking gas exhaust pipe (5) located after the exhaust temperature sensor (7).

2. The on-line real flow test device for the leakage of aircraft high temperature and high pressure valves according to claim 1 is characterized in that: The leaked gas collecting box (2) comprises two splicing pieces (21); each of the two ends of the splicing piece (21) has a half hoop piece (212); the half hoop piece (212) comprises a semi-cylindrical tube (2121) and two transverse plates (2122); the two transverse plates (2122) are respectively connected to two sides of the semi-cylindrical tube (2121); the two transverse plates (2122) are on the same plane, and the plane passes through the axis of the semi-cylindrical tube (2121); The aircraft high-temperature and high-pressure valve leakage online real-flow test device further comprises two port seals (9); each of the port seals (9) comprises 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); The two port seals (9) are respectively tightly sleeved on the air inlet pipe (1) and the air outlet pipe (3) by the circular sleeve (901); the half hoop pieces (212) at both ends of each splicing piece (21) are fitted to the same side of the two port seals (9), including the semi-cylindrical tube (2121) fitting the circular sleeve (901), and the two transverse plates (2122) fitting the two fins (902); the half hoop pieces (212) at the same end of the two splicing pieces (21) clamp the same port seal (9), including each of the two opposite transverse plates (2122) clamping one fin (902), and a plurality of bolts are passed through the two transverse plates (2122) and one fin (902) to seal and lock.

3. The on-line real flow test device for the leakage of aircraft high temperature and high pressure valves according to claim 2 is characterized in that: Each of the splicing pieces (21) is installed with a group of the cooling pieces; the cooling pieces include coils (213); the splicing piece (21) has a double-layer structure, and the coils (213) are evenly arranged in the double-layer structure; and the two groups of coils (213) avoid the three openings of the leaking gas collecting box (2).

4. The on-line real flow test device for the leakage of high temperature and high pressure valve of aircraft according to claim 3 is characterized in that: The aircraft high-temperature and high-pressure valve leakage online real-flow test device further comprises two side seals (10); the side seals (10) are U-shaped; each of the splicing pieces (21) has a U-shaped side (2111); each of the side seals (10) is fitted between the U-shaped side (2111) on the same side of the two splicing pieces (21); the two ends of the side seals (10) are butt-jointed with the two fins (902), and the side seals (10) and the fins (902) are sealed and connected using high-temperature resistant glue; and a plurality of bolts are passed through the U-shaped side (2111) of the two splicing pieces (21) and the side seals (10) to seal and fix them.

5. The on-line real flow test device for the leakage of high temperature and high pressure valve of aircraft according to claim 3, characterized in that: The leaked 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; when the cooling water tank is filled with water, the spiral pipe section can be submerged; the cooling water tank is connected to a water inlet pipe and a drain pipe.

6. An online real-flow test method for the leakage of an aircraft high-temperature and high-pressure valve, characterized in that: The online real flow test device for the leakage of the aircraft high temperature and high pressure valve according to claim 3 or 4 is used for testing; the online real flow test method for the leakage of the aircraft high temperature and high pressure valve comprises: Assembly stage: the two port seals (9) are placed outside the air inlet pipe (1) and the air outlet pipe (3); the connector of the high-temperature and high-pressure valve on the aircraft is removed, the air inlet pipe (1) is connected to the air inlet of the high-temperature and high-pressure valve online, and the air outlet pipe (3) is connected to the air outlet of the high-temperature and high-pressure valve; the two splicing pieces (21) are wrapped outside the high-temperature and high-pressure valve, the high-temperature and high-pressure valve is located in the middle of the internal space of the two splicing pieces (21) connected together, and the half hoop pieces (212) of the two splicing pieces (21) are aligned. The port seal (9) fixes the two ends of the two splicing pieces (21) to the two port seals (9) respectively, and seals the U-shaped sides (2111) of the two splicing pieces (21) so that the two splicing pieces (21) are relatively sealed and connected; installs 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); introduces cooling water into each group of the coils (213); and starts the cooling device (6); The first test stage: hot air with a temperature of 380°C to 420°C and an air pressure of 164psi to 223psi is introduced into the air inlet pipe (1), and the ambient temperature sensor (4) senses a temperature of T1. If T1<80°C, the cooling water flow rate of each group of the coils (213) is reduced until T1 is between 80°C and 140°C; if T1>140°C, the cooling water flow rate of each group of the coils (213) is increased until T1 is between 80°C and 140°C; the exhaust temperature sensor (7) senses a temperature of T2. If T2≥50°C, the cooling device (6) is adjusted until T2<50°C; when T1 is between 80°C and 140°C and T2<50°C, after the reading of the flow meter (8) is stable, the stable flow reading of the flow meter (8) is read as the leakage of the high-temperature and high-pressure valve.

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

8. The on-line real flow test method for the leakage of an aircraft high temperature and high pressure valve according to claim 6 or 7, characterized in that: After the reading of the flow meter (8) is stabilized, specifically, the difference between the highest and lowest flow readings of the flow meter (8) within 30 seconds does not exceed 2 L / min, and the stable flow reading is the last reading at the end of the 30 seconds.

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

10. An online real-flow test method for the leakage of an aircraft high-temperature and high-pressure valve, characterized in that: The test is performed using the on-line real-flow test device for the leakage of the aircraft high-temperature and high-pressure valve as described in claim 5; the on-line real-flow test method for the leakage of the aircraft high-temperature and high-pressure valve comprises: introducing hot air into the air inlet pipe (1), the exhaust temperature sensor (7) senses a temperature T2, and if T2 ≥ 50°C, the cooling water flow rate of the cooling water tank is accelerated so that T2 < 50°C.

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