Device for detecting sealing performance of aircraft engine fuel system

Abstract

The utility model relates to the technical field of sealing detection, and provides a device for detecting the sealing performance of an aircraft engine fuel system, which comprises a detection table, two electric sliding rails are symmetrically and fixedly arranged at the bottom of the detection table, an inverted T-shaped plate is connected onto the electric sliding rails in a sliding manner through sliding blocks, and the inverted T-shaped plate and a first inverted U-shaped plate are driven to move through the electric sliding rails. When the rectangular shells are located under the lifting assembly, the lifting assembly drives the multiple sealing detection mechanisms to descend at the same time, so that fuel nozzles on the first row of rectangular shells can be sealed, inflation and airtightness detection of a high-temperature gas tank are facilitated, and after completion, an electric sliding rail continues to drive an inverted T-shaped plate and a first inverted U-shaped plate to move; the above steps are repeated, so that the remaining fuel nozzles on the rectangular shell can be detected, a plurality of fuel nozzles can be detected at the same time, the detection efficiency is effectively improved, and meanwhile the situation that the time consumed in the detection process is long is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of sealing detection, in particular to a device for detecting the sealing performance of a fuel system of an aircraft engine. Background Art

[0002] The fuel nozzle is a key component of the aircraft engine. Its sealing quality is not only related to the technical performance of the fuel system, but also directly related to the safety of the aircraft during flight. Therefore, a sealing test must be carried out after the fuel nozzle is assembled.

[0003] Known Chinese public authorized utility model CN218765857U discloses an aircraft engine fuel nozzle sealing detection device, including a device base plate, a first bracket, a cylindrical bracket is provided on the first bracket, a second bracket is provided on the top of the device base plate, a cylindrical bracket is provided on the second bracket, a high-temperature gas tank is provided on the top of the device base plate, and two mechanical arms are provided on the second bracket. The utility model is provided with a first sealing rubber plate, a high-temperature gas tank, a second sealing rubber plate, a mechanical arm, a pressure wheel, and a gas nozzle. The nozzle is supported by the first bracket and the second bracket and the front and rear openings of the nozzle are sealed with the first sealing rubber plate and the second sealing rubber plate, so that the gas nozzle sprays the high-temperature gas in the high-temperature gas tank into the nozzle. At the same time, the pressure wheel applies rolling pressure to the nozzle to simulate the high-pressure environment in the engine, thereby effectively detecting the sealing and structural strength of the fuel nozzle.

[0004] However, in the implementation of related technologies, it was found that the above solution had the following problems: the detection efficiency was low and the fuel nozzles could not be tested in batches, which resulted in a long detection process and affected the overall production and processing efficiency. Utility Model Content

[0005] The utility model provides a device for detecting the sealing of an aircraft engine fuel system, which solves the problems in the related art of low detection efficiency and inability to detect fuel nozzles in batches, resulting in a long detection process and affecting the overall production and processing efficiency.

[0006] The technical solution of the utility model is as follows: A device for testing the sealing of an aircraft engine fuel system comprises a test platform, wherein two electric slide rails are symmetrically fixedly mounted on the bottom of the test platform, and an inverted T-plate is slidably connected to the electric slide rails via a slider. A first inverted U-plate is provided above the test platform, and the two ends of the first inverted U-plate pass through a strip groove on the test platform and are fixedly connected to the inverted T-plate.

[0007] A plurality of rectangular shells are fixedly mounted on the top of the first inverted U-plate in a longitudinal arrangement, and a plurality of gas nozzles are fixedly mounted on the top of the plurality of rectangular shells in sequence from left to right;

[0008] A lifting assembly, a high-temperature gas tank, and a cooler are fixedly installed on the top of the test bench, and a plurality of sealing detection mechanisms are fixedly installed on the lifting assembly from left to right.

[0009] A plurality of transition assemblies are fixedly installed on the inner side of the first inverted U-plate in a longitudinal arrangement, and the transition assemblies are connected to the first inverted U-plate. Conveying assemblies are provided at both ends of the transition assemblies, and the plurality of transition assemblies are connected through the conveying assemblies. The high-temperature gas tank and the cooler are connected to the conveying assemblies through hoses.

[0010] Preferably, first electric telescopic rods are fixedly mounted on both sides of the inner wall of the lifting assembly, a fixed frame is fixedly mounted on one end of the first electric telescopic rod, and an elastic mechanism is provided on the inner side of the fixed frame;

[0011] A T-shaped plug-in plate is installed at one end of the elastic mechanism, plug-in slots are provided on both sides of the first inverted U-plate, and the other end of the T-shaped plug-in plate is plugged into the plug-in slot.

[0012] Preferably, the elastic mechanism includes a limiting rod movably plugged into the fixed frame, an outer side wall of the limiting rod is provided with a spring, and the spring is located between the fixed frame and the T-shaped plug plate.

[0013] Preferably, the lifting assembly includes a second inverted U-frame fixedly mounted on the top of the detection platform, a second electric telescopic rod is fixedly mounted through the second inverted U-frame, a connecting plate is fixedly mounted on the bottom of the second electric telescopic rod, and the sealing detection mechanism is fixedly mounted on the bottom of the connecting plate.

[0014] Preferably, the transition assembly includes three hollow tubes arranged on the inner side of the first inverted U-plate, and the three hollow tubes are connected by the conveying assembly;

[0015] A plurality of branch pipes are fixedly mounted on the outer side wall of the hollow tube, and the other ends of the branch pipes pass through a side wall of the first inverted U-plate and are connected to the rectangular shell.

[0016] Preferably, the conveying assembly includes two first connecting rods installed through both sides of the first inverted U-plate, and the high-temperature gas tank and the cooler are connected to the first connecting rods through hoses;

[0017] A four-way joint is fixedly installed on the other end of the first connecting rod, and a second connecting rod is fixedly installed on the other two ends of the four-way joint. A elbow joint is fixedly installed on the other end of the second connecting rod, and the three hollow tubes are respectively connected to the first connecting rod and the elbow joint.

[0018] Preferably, a solenoid valve 1 is fixedly installed on each of the plurality of hollow tubes.

[0019] Preferably, an exhaust pipe is fixedly mounted on one side of the rectangular shell, and a second solenoid valve is provided on the outer side wall of the exhaust pipe.

[0020] The working principle and beneficial effects of the utility model are as follows:

[0021] The inverted T-plate and the first inverted U-plate are moved by the electric slide rail. When the rectangular shell is located directly below the lifting assembly, the lifting assembly simultaneously drives multiple sealing detection mechanisms to descend, so that the fuel nozzles on the first row of rectangular shells can be sealed, thereby facilitating the inflation and airtightness testing of the high-temperature gas tanks. After completion, the electric slide rail continues to drive the inverted T-plate and the first inverted U-plate to move, and then repeats the above steps, so that the fuel nozzles on the remaining rectangular shells can be tested, and multiple fuel nozzles can be tested at the same time, which effectively improves the detection efficiency and reduces the time-consuming detection process. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The present invention will be further described in detail below with reference to the accompanying drawings and specific implementation methods.

[0023] Figure 1 This is a schematic diagram of the overall structure proposed by the utility model;

[0024] Figure 2 This is a schematic diagram of the structure of the electric slide rail proposed in the utility model;

[0025] Figure 3 This is a schematic diagram of the structure of the conveying assembly proposed in the utility model;

[0026] Figure 4 This is a schematic diagram of the structure of the lifting assembly proposed in the utility model;

[0027] Figure 5 This is a schematic structural diagram of the first electric telescopic rod proposed in the utility model;

[0028] In the figure: 1. Test table; 2. Electric slide rail; 3. Inverted T-plate; 4. First inverted U-plate; 5. Rectangular shell; 6. Gas nozzle;

[0029] 7. Lifting assembly; 71. Second inverted U-frame; 72. Second electric telescopic rod; 73. Connecting plate;

[0030] 8. Sealing detection mechanism; 9. High-temperature gas tank; 10. Cooling machine;

[0031] 11. Conveying assembly; 1101. First connecting rod; 1102. Cross joint; 1103. Second connecting rod; 1104. Elbow joint;

[0032] 12. Transition assembly; 1201. Hollow tube; 1202. Branch pipe;

[0033] 13. First electric telescopic rod; 14. Fixed frame; 15. T-shaped plug plate; 16. Insertion slot; 17. Limit rod; 18. Spring. DETAILED DESCRIPTION

[0034] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0035] Example 1

[0036] See also Figure 1 - Figure 5 A device for testing the sealing performance of an aircraft engine fuel system comprises a test platform 1, two electric slide rails 2 being symmetrically fixedly mounted on the bottom of the test platform 1, an inverted T-plate 3 being slidably connected to the electric slide rails 2 via sliders, a first inverted U-plate 4 being disposed above the test platform 1, and both ends of the first inverted U-plate 4 passing through strip grooves on the test platform 1 and being fixedly connected to the inverted T-plate 3;

[0037] A plurality of rectangular shells 5 are fixedly mounted on the top of the first inverted U-plate 4 in a longitudinal arrangement. A plurality of gas nozzles 6 are fixedly mounted on the top of the plurality of rectangular shells 5 from left to right. An exhaust pipe is fixedly mounted on one side of the rectangular shell 5. A second solenoid valve is provided on the outer side wall of the exhaust pipe.

[0038] A lifting assembly 7, a high-temperature gas tank 9, and a cooler 10 are fixedly mounted on the top of the test bench 1. Multiple sealing detection mechanisms 8 are fixedly mounted on the lifting assembly 7 from left to right.

[0039] A plurality of transition assemblies 12 are fixedly installed on the inner side of the first inverted U-plate 4 in a longitudinal arrangement, and the transition assemblies 12 are connected to the first inverted U-plate 4. Conveying assemblies 11 are provided at both ends of the transition assemblies 12, and the plurality of transition assemblies 12 are connected through the conveying assemblies 11. The high-temperature gas tank 9 and the cooler 10 are connected to the conveying assemblies 11 through hoses.

[0040] The utility model provides a device for detecting the sealing of the fuel system of an aircraft engine. When in use, the fuel nozzle is manually placed on the gas nozzle 6 on the rectangular shell 5, and the rectangular shell 5 with one end opening of the nozzle is tightly fitted. Then, the inverted T plate 3 and the first inverted U plate 4 are driven to move by the electric slide rail 2. When the first row of rectangular shells 5 are located directly below the lifting component 7, the lifting component 7 simultaneously drives multiple sealing detection mechanisms 8 to descend, so that the fuel nozzles on the first row of rectangular shells 5 can be sealed. Then, the valve on the high-temperature gas tank 9 is opened to allow high-pressure and high-temperature gas to enter the rectangular shell 5 from the hose, the delivery component 11 and the transition component 12, and then the rectangular shell 5 is opened. The gas in the rectangular shell 5 is then sprayed into the interior of the nozzle under test from the gas nozzle 6, so that the fuel nozzle can be sealed. After the test is completed, the solenoid valve 2 is opened to allow the gas in the rectangular shell 5 to be discharged from the exhaust pipe, and then the cooler 10 is started to cool the nozzle. After completion, the sealing detection mechanism 8 is driven to rise by the lifting component 7, and then the electric slide rail 2 continues to drive the inverted T plate 3 and the first inverted U plate 4 to move, and then the above steps are repeated, so that the fuel nozzles on the remaining rectangular shells 5 can be tested, and then multiple fuel nozzles can be tested at the same time, which effectively improves the detection efficiency and reduces the time-consuming detection process.

[0041] Furthermore, the lifting assembly 7 includes a second inverted U-frame 71 fixedly mounted on the top of the detection platform 1, a second electric telescopic rod 72 is fixedly mounted through the second inverted U-frame 71, a connecting plate 73 is fixedly mounted at the bottom of the second electric telescopic rod 72, and the sealing detection mechanism 8 is fixedly mounted at the bottom of the connecting plate 73.

[0042] Specifically, the second electric telescopic rod 72 drives the connecting plate 73 to descend, so that the sealing detection mechanism 8 can seal the fuel nozzle.

[0043] Furthermore, the transition assembly 12 includes three hollow tubes 1201 arranged inside the first inverted U-plate 4, and the three hollow tubes 1201 are connected by the conveying assembly 11;

[0044] A plurality of branch pipes 1202 are fixedly mounted on the outer wall of the hollow tube 1201 , and the other ends of the branch pipes 1202 pass through a side wall of the first inverted U-plate 4 and are connected to the rectangular shell 5 .

[0045] Specifically, through the hollow tube 1201 and the branch tube 1202 , the gas can enter the rectangular shell 5 from the hose and the delivery assembly 11 , so that multiple fuel nozzles can be tested simultaneously.

[0046] Furthermore, the conveying assembly 11 includes two first connecting rods 1101 installed on both sides of the first inverted U-plate 4, and the high-temperature gas tank 9 and the cooler 10 are connected to the first connecting rods 1101 through hoses;

[0047] The other end of the first connecting rod 1101 is fixedly installed with a four-way joint 1102, the other two ends of the four-way joint 1102 are fixedly installed with a second connecting rod 1103, the other end of the second connecting rod 1103 is fixedly installed with an elbow joint 1104, and the three hollow tubes 1201 are respectively connected between the first connecting rod 1101 and the elbow joint 1104.

[0048] Specifically, when the gas enters the four-way joint 1102 through the first connecting rod 1101, the gas can be diverted through the four-way joint 1102, the second connecting rod 1103 and the elbow joint 1104, so that the gas can flow into multiple transition assemblies 12, and then detect multiple fuel nozzles respectively.

[0049] Furthermore, a solenoid valve 1 is fixedly installed on each of the multiple hollow tubes 1201.

[0050] Specifically, when the fuel nozzles on the first row of rectangular shells 5 are inspected, the solenoid valve 1 on the hollow tube 1201 corresponding to the first row of rectangular shells 5 is opened, so that the fuel nozzles can be inspected at the same time, and the fuel nozzles on the gas row can be prevented from being blown off due to the lack of downward pressure sealing by the lifting assembly 7 and the sealing detection mechanism 8.

[0051] Example 2

[0052] Based on the first embodiment, in this embodiment: a first electric telescopic rod 13 is fixedly mounted on both sides of the inner wall of the lifting assembly 7, a fixed frame 14 is fixedly mounted on one end of the first electric telescopic rod 13, and an elastic mechanism is provided on the inner side of the fixed frame 14;

[0053] A T-shaped inserting plate 15 is installed at one end of the elastic mechanism. Inserting grooves 16 are provided on both sides of the first inverted U-plate 4 , and the other end of the T-shaped inserting plate 15 is inserted into the inserting groove 16 .

[0054] The technical solution provided by this embodiment is: when the T-shaped plug-in plate 15 is level with the plug-in slot 16 on the first inverted U-plate 4, the T-shaped plug-in plate 15 is inserted into the plug-in slot 16 under the action of the elastic mechanism, so that the rectangular shell 5 and the gas nozzle 6 can be accurately located directly below the lifting assembly 7 and the sealing detection mechanism 8. When the detection of the first row of rectangular shells 5 is completed, the fixed frame 14 is driven by the retracted first electric telescopic rod 13, so that the T-shaped plug-in plate 15 can be pulled out of the plug-in slot 16, and then the electric slide rail 2 can continue to drive the inverted T-plate 3 and the first inverted U-plate 4 to move. While moving, the first electric telescopic rod 13 drives the fixed frame 14 to extend. When the plug-in slot 16 on the first inverted U-plate 4 is level with the T-shaped plug-in plate 15 again, the T-shaped plug-in plate 15 will be inserted into the plug-in slot 16 again.

[0055] Furthermore, the elastic mechanism includes a limiting rod 17 movably plugged into the fixed frame 14 . A spring 18 is provided on the outer side wall of the limiting rod 17 , and the spring 18 is located between the fixed frame 14 and the T-shaped plug plate 15 .

[0056] Specifically, the T-shaped inserting plate 15 is pushed by the elastic force of the spring 18 , so that the T-shaped inserting plate 15 can move stably under the action of the limiting rod 17 and the fixing frame 14 .

[0057] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A device for detecting the sealing performance of an aircraft engine fuel system, comprising a detection platform (1), characterized in that: Two electric slide rails (2) are symmetrically fixedly installed at the bottom of the detection platform (1), and an inverted T-plate (3) is slidably connected to the electric slide rails (2) via a slider. A first inverted U-plate (4) is provided above the detection platform (1), and both ends of the first inverted U-plate (4) pass through the strip groove on the detection platform (1) and are fixedly connected to the inverted T-plate (3); A plurality of rectangular shells (5) are fixedly mounted in sequence and arranged longitudinally on the top of the first inverted U-plate (4); a plurality of gas nozzles (6) are fixedly mounted in sequence from left to right on the top of the plurality of rectangular shells (5); A lifting assembly (7), a high-temperature gas tank (9) and a cooling machine (10) are fixedly mounted on the top of the detection platform (1), and a plurality of sealing detection mechanisms (8) are fixedly mounted on the lifting assembly (7) in sequence from left to right; A plurality of transition assemblies (12) are fixedly installed in sequence and arranged longitudinally on the inner side of the first inverted U plate (4), and the transition assemblies (12) are connected to the first inverted U plate (4). Conveying assemblies (11) are provided at both ends of the transition assemblies (12), and the plurality of transition assemblies (12) are connected to each other through the conveying assemblies (11). The high-temperature gas tank (9) and the cooler (10) are connected to the conveying assemblies (11) through a hose.

2. The device for detecting the sealing performance of an aircraft engine fuel system according to claim 1, characterized in that: A first electric telescopic rod (13) is fixedly mounted on both sides of the inner wall of the lifting assembly (7), a fixed frame (14) is fixedly mounted on one end of the first electric telescopic rod (13), and an elastic mechanism is provided on the inner side of the fixed frame (14); A T-shaped plug-in plate (15) is installed at one end of the elastic mechanism, plug-in slots (16) are provided on both sides of the first inverted U-plate (4), and the other end of the T-shaped plug-in plate (15) is plugged into the plug-in slot (16).

3. The device for detecting the sealing performance of an aircraft engine fuel system according to claim 2, characterized in that: The elastic mechanism comprises a limiting rod (17) movably plugged into the fixed frame (14); a spring (18) is provided on the outer side wall of the limiting rod (17), and the spring (18) is located between the fixed frame (14) and the T-shaped plug plate (15).

4. The device for detecting the sealing performance of an aircraft engine fuel system according to claim 1, characterized in that: The lifting assembly (7) comprises a second inverted U-frame (71) fixedly mounted on the top of the detection platform (1); a second electric telescopic rod (72) is fixedly mounted through the second inverted U-frame (71); a connecting plate (73) is fixedly mounted at the bottom of the second electric telescopic rod (72); and the sealing detection mechanism (8) is fixedly mounted at the bottom of the connecting plate (73).

5. The device for detecting the sealing performance of an aircraft engine fuel system according to claim 1, characterized in that: The transition component (12) comprises three hollow tubes (1201) arranged on the inner side of the first inverted U-plate (4), and the three hollow tubes (1201) are connected via the conveying component (11); A plurality of branch pipes (1202) are fixedly mounted on the outer side wall of the hollow tube (1201), and the other ends of the branch pipes (1202) pass through a side wall of the first inverted U-plate (4) and are connected to the rectangular shell (5).

6. The device for detecting the sealing performance of an aircraft engine fuel system according to claim 5, characterized in that: The conveying assembly (11) comprises two first connecting rods (1101) installed through both sides of the first inverted U-plate (4), and the high-temperature gas tank (9) and the cooler (10) are both connected to the first connecting rods (1101) via hoses; A four-way joint (1102) is fixedly installed on the other end of the first connecting rod (1101), and a second connecting rod (1103) is fixedly installed on the other two ends of the four-way joint (1102). A bend pipe joint (1104) is fixedly installed on the other end of the second connecting rod (1103), and the three hollow tubes (1201) are respectively connected to the first connecting rod (1101) and the bend pipe joint (1104).

7. The device for detecting the sealing performance of an aircraft engine fuel system according to claim 6, characterized in that: A solenoid valve 1 is fixedly installed on each of the plurality of hollow tubes (1201).

8. The device for detecting the sealing performance of an aircraft engine fuel system according to claim 1, characterized in that: An exhaust pipe is fixedly mounted on one side of the rectangular shell (5), and a second solenoid valve is provided on the outer side wall of the exhaust pipe.

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