Fuel nozzle detection equipment for aero-engine

Abstract

The invention discloses fuel nozzle detection equipment for an aero-engine, and relates to the technical field of fuel nozzle detection, and the fuel nozzle detection equipment comprises a detection equipment body, the left and right sides of the upper part of the detection equipment body are both provided with supporting plates, and the lower part of a top plate is provided with a fuel separator assembly through a first electric telescopic rod. A circulating water pump is mounted on the right side of the right supporting plate; and a connecting plate is mounted between the supporting plates. The fuel nozzle detection equipment for the aero-engine is provided with the metering cylinder, after the sealing performance of a fuel nozzle is detected, the baffle can be driven to rotate through the damping rotating piece, the baffle can be rotated more easily by pressing down an anti-skid block, a through hole covered by the baffle is leaked out, and the sealing performance of the fuel nozzle is improved. Liquid in the fuel nozzle can fall into the metering cylinder through the through hole, the flow of the fuel nozzle is detected through the metering cylinder, and therefore the sealing performance and the flow of the fuel nozzle can be detected.

Description

Technical Field

[0001] The present invention relates to the technical field of fuel nozzle detection, and particularly to a fuel nozzle detection device for an aero-engine. Background Technique

[0002] The fuel nozzle for an aero-engine is a key component, mainly used for atomizing or vaporizing fuel, accelerating the formation of the mixture, ensuring stable combustion and improving combustion efficiency. The fuel nozzle scatters the fuel finely into the combustion chamber through the flow channel constraint, mixes with air and then burns and expands to do work, pushing the aircraft into the sky.

[0003] Common types of fuel nozzles used on aero-engines include centrifugal nozzles, pneumatic nozzles, evaporation nozzles, and oil slinger nozzles, etc. Each nozzle has its specific function and applicable scenario.

[0004] The working principle of the fuel nozzle is to inject fuel into the nozzle under high pressure, use a specific flow channel design to atomize or vaporize the fuel, mix it with compressed air and then enter the combustion chamber for combustion. Different types of nozzles are suitable for different combustion chamber designs and flight conditions. In order to ensure the normal use of the fuel nozzle, it is necessary to detect the fuel nozzle before installation.

[0005] For example, the Chinese utility model patent with the application number 202420655909.X discloses a lubricating oil nozzle detection device for an aero-engine. By driving the oil distributor, oil pipes, and rack plate up and down with an electric push rod, it can quickly install and fix or release the fixation of multiple fuel injectors during the detection process, so as to realize the quick installation and disassembly of the fuel injectors, making it more convenient for the staff to operate and enabling quick detection of the fuel injectors, thus improving the detection efficiency. However, there are still certain defects in its device;

[0006] It is not convenient to clean the inside of the graduated cylinder. The internal dirt accumulated in the graduated cylinder is likely to cause errors in the measurement of the graduated cylinder, thereby reducing the detection accuracy of the nozzle flow rate. At the same time, the sealing performance of the nozzle cannot be detected.

[0007] Therefore, we propose a fuel nozzle detection device for an aero-engine to solve the problems raised above. Summary of the Invention

[0008] The purpose of the present invention is to provide a fuel nozzle detection device for an aero-engine to solve the problems in the above background technique that it is not convenient to clean the inside of the graduated cylinder in the current market, the internal dirt accumulated in the graduated cylinder is likely to cause errors in the measurement of the graduated cylinder, thereby reducing the detection accuracy of the nozzle flow rate, and at the same time, the sealing performance of the nozzle cannot be detected.

[0009] To achieve the above object, the present invention provides the following technical solution: A fuel nozzle detection device for an aeroengine, comprising a detection device body. On the upper left and right sides of the detection device body, support plates are installed, and a top plate is installed above the support plates. Below the top plate, a fuel distributor assembly is installed through a first electric telescopic rod. On the right side of the right support plate, a circulating water pump is installed;

[0010] A connecting plate is installed between the support plates, and a placement pipe is installed on the connecting plate. On the right side of the left support plate, a movable strip is installed through a second electric telescopic rod. On the movable strip, a positioning block assembly is installed at equal intervals. On the movable strip, through holes are opened at equal intervals, and damping rotating parts are installed at equal intervals on the movable strip. Moreover, a baffle is installed on the damping rotating part. Above the baffle, a sealing block is installed through a telescopic spring, and anti-sliding blocks are installed on the left and right sides below the sealing block;

[0011] A hollow frame is installed on the upper surface of the detection device body. On the left side of the left support plate, a servo motor is installed. On the right side of the servo motor, a transmission shaft is installed through an output shaft. On the upper and lower sides of the transmission shaft, fixing blocks are installed, and at the ends of the fixing blocks far from the transmission shaft, metering cylinders are installed through threaded connectors;

[0012] A first conical gear is installed on the transmission shaft. A fixed shaft is installed on the upper surface of the detection device body, and a rotating shaft is sleeved on the fixed shaft. At the upper end of the rotating shaft, a second conical gear is installed. On the right side of the left support plate, a connecting block is installed, and a winding rope is installed on the connecting block.

[0013] Preferably, an inlet pipe and an outlet pipe are respectively installed above and below the circulating water pump. A detection liquid tank is installed above the detection device body.

[0014] With the above structural design, the circulating water pump conveys the liquid in the detection liquid tank.

[0015] Preferably, the inlet pipe is communicated with the inside of the detection liquid tank, the outlet pipe is communicated with the inside of the fuel distributor assembly, and the outlet pipe is designed as a telescopic structure.

[0016] With the above structural design, when the circulating water pump is started, the circulating water pump pumps out the liquid in the detection liquid tank through the inlet pipe, and then conveys the liquid to the fuel distributor assembly through the outlet pipe. The fuel distributor assembly conveys the liquid into the fuel nozzle for the aeroengine fixed in the placement pipe to detect the fuel nozzle for the aeroengine.

[0017] Preferably, both the upper and lower ends of the placement pipe are designed as open structures. There are multiple placement pipes, and the number of the positioning block assemblies is equal to the number of the placement pipes.

[0018] With the above structural design, the fuel nozzle of the aero-engine is placed inside the placement tube, and the fuel nozzle is pressed downward to drive the sealing block to move downward. At this time, the telescopic spring is in a compressed state. Then, the second electric telescopic rod is started, and the second electric telescopic rod drives the movable strip to move to the right. The movable strip drives the positioning block assembly to move to the right to clamp and fix the fuel nozzle in the placement tube, thus facilitating the fixation of the fuel nozzle.

[0019] Preferably, the positioning block assembly is slidably connected to the placement tube. A limit block is installed on the left side of the right support plate, and a limit groove is formed on the left side of the limit block. The movable strip is slidably connected to the limit groove.

[0020] With the above structural design, when the positioning block assembly moves to the right under force, the fuel nozzle can be fixed. When the movable strip is under force, it can move left and right along the limit groove on the limit block, making the movement of the movable strip more stable when it moves left and right.

[0021] Preferably, the damping rotating part is located at the upper right position of the through hole, and the positioning block assembly is located at the upper left position of the through hole. When the baffle coincides with the through hole, the baffle covers the through hole, and the baffle is subjected to anti-rust treatment.

[0022] With the above structural design, after the sealing performance detection of the fuel nozzle is completed, the baffle can be driven to rotate through the damping rotating part. By pressing down the anti-sliding block, it is easier to rotate the baffle, and the through hole covered by the baffle is exposed.

[0023] Preferably, the shape of the sealing block is designed according to the shape of the fuel nozzle to be detected. The elastic force of the telescopic spring is less than the clamping force of the positioning block assembly on the fuel nozzle when it is under force. A groove is formed on the front surface of the anti-sliding block.

[0024] With the above structural design, the sealing block seals the ejection end of the fuel nozzle under the action of the resilience of the telescopic spring, thus facilitating the detection of the sealing performance of the fuel nozzle.

[0025] Preferably, the threaded connecting piece includes a threaded sleeve and a bolt. The threaded connecting piece is connected to the fixed block, the threaded sleeve is connected to the measuring cylinder, the threaded sleeve and the bolt are in threaded connection. There are multiple measuring cylinders and fixed blocks. The center line of the measuring cylinder coincides with the center line of the through hole. The forward and reverse rotation of the servo motor is controllable. A drainage pipe is connected to the rear side of the hollow frame.

[0026] With the above structural design, after the flow rate of the fuel nozzle is detected, the servo motor is started. The servo motor drives the transmission shaft to rotate through the output shaft, and the transmission shaft drives the measuring cylinder to rotate by 90°. During the rotation of the liquid in the upper measuring cylinder, the liquid inside it can fall into the hollow frame and be discharged through the drainage pipe in the hollow frame, which is convenient for cleaning the measuring cylinder. When deep cleaning of the measuring cylinder is required, the upper measuring cylinder is removed through the threaded connection, and then the transmission shaft is driven to rotate by the servo motor to expose the lower measuring cylinder, thus not affecting the progress of the flow rate detection of the fuel nozzle.

[0027] Preferably, the rotating shaft is rotatably connected to the fixed shaft. The rotating shaft and the fixed shaft are located on the left side of the hollow frame. A second bevel gear is installed at the upper end of the rotating shaft, and the second bevel gear is perpendicular to and meshes with the first bevel gear.

[0028] With the above structural design, when the rotating shaft rotates, it can drive the first bevel gear to rotate, the first bevel gear drives the second bevel gear to rotate, and the second bevel gear drives the rotating shaft to rotate.

[0029] Preferably, the end of the winding rope is detachably connected to the rotating shaft, and the length of the winding rope is set according to actual use.

[0030] With the above structural design, when the rotating shaft rotates, the rotating shaft can wind up the winding rope. The number of times the measuring cylinder is used can be estimated according to the winding situation of the winding rope, so as to facilitate timely deep cleaning of the measuring cylinder and improve the service life of the measuring cylinder. After the deep cleaning of the measuring cylinder is completed, the end of the winding rope can be detached from the rotating shaft and reconnected.

[0031] Compared with the prior art, the beneficial effects of the present invention are as follows: The fuel nozzle detection device for an aeroengine:

[0032] 1. A measuring cylinder is provided. After the sealing performance of the fuel nozzle is detected, the baffle can be driven to rotate through the damping rotating part, and the anti-sliding block can be pressed down to make it easier to rotate the baffle, so that the through hole covered by the baffle is exposed. The liquid in the fuel nozzle can fall into the measuring cylinder through the through hole, and the flow rate of the fuel nozzle is detected through the measuring cylinder, so as to realize the detection of both the sealing performance and the flow rate of the fuel nozzle.

[0033] 2. A drive shaft is provided. After the flow rate of the fuel nozzle is detected, the servo motor is started. The servo motor drives the drive shaft to rotate through the output shaft, and the drive shaft drives the metering cylinder to rotate by 90°. During the rotation of the upper metering cylinder, the liquid inside it can fall into the hollow frame and be discharged through the drainage pipe in the hollow frame, which is convenient for cleaning the metering cylinder. When deep cleaning of the metering cylinder is required, the upper metering cylinder is removed through the threaded connection, and then the drive shaft is driven to rotate by the servo motor to expose the lower metering cylinder, so as not to affect the progress of the flow rate detection of the fuel nozzle;

[0034] 3. A winding rope is provided. When the rotating shaft rotates, the rotating shaft can wind up the winding rope, and the number of uses of the metering cylinder can be estimated according to the winding situation of the winding rope, so as to facilitate the timely deep cleaning of the metering cylinder and improve the service life of the metering cylinder. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 is a schematic partial cross-sectional structure diagram of the present invention;

[0036] Figure 2 is a schematic front view structure diagram of the present invention;

[0037] Figure 3 is of the present invention Figure 1 is an enlarged structure diagram at A in the present invention.

[0038] Figure 4 is of the present invention Figure 1 is an enlarged structure diagram at B in the present invention;

[0039] Figure 5 is of the present invention Figure 1 is an enlarged structure diagram at C in the present invention;

[0040] Figure 6 is a schematic structure diagram when the fuel nozzle of the present invention is subjected to a sealing performance test;

[0041] Figure 7 is a schematic structure diagram when the fuel nozzle of the present invention is subjected to a flow rate test;

[0042] Figure 8 is a schematic installation structure diagram of the sealing block of the present invention;

[0043] Figure 9 is a schematic connection structure diagram of the threaded connection member and the metering cylinder of the present invention;

[0044] Figure 10 is a schematic structure diagram of the lower surface of the movable bar of the present invention.

[0045] In the figure: 1. Detection device body; 2. Support plate; 3. Top plate; 4. First electric telescopic rod; 5. Oil distributor assembly; 6. Circulating water pump; 7. Water inlet pipe; 8. Water outlet pipe; 9. Detection liquid tank; 10. Connecting plate; 11. Placing pipe; 12. Second electric telescopic rod; 13. Movable strip; 14. Positioning block assembly; 15. Through hole; 16. Damping rotating part; 17. Baffle; 18. Telescopic spring; 19. Sealing block; 20. Anti-slip block; 21. Limit block; 22. Limit groove; 23. Hollow frame; 24. Servo motor; 25. Transmission shaft; 26. Fixed block; 27. Threaded connecting piece; 28. Measuring cylinder; 29. First bevel gear; 30. Fixed shaft; 31. Rotating shaft; 32. Second bevel gear; 33. Connecting block; 34. Winding rope. Detailed implementation manners

[0046] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0047] Please refer to Figures 1 - 10, the present invention provides a technical solution: a fuel nozzle detection device for an aeroengine, comprising a detection device body 1, a support plate 2, a top plate 3, a first electric telescopic rod 4, an oil distributor assembly 5, a circulating water pump 6, a water inlet pipe 7, a water outlet pipe 8, a detection liquid tank 9, a connecting plate 10, a placement pipe 11, a second electric telescopic rod 12, a movable bar 13, a positioning block assembly 14, a through hole 15, a damping rotating member 16, a baffle 17, a telescopic spring 18, a sealing block 19, an anti-slip block 20, a limiting block 21, a limiting groove 22, a hollow frame 23, a servo motor 24, a transmission shaft 25, a fixed block 26, a threaded connector 27, a measuring cylinder 28, a first bevel gear 29, a fixed shaft 30, a rotating shaft 31, a second bevel gear 32, a connecting block 33 and a winding rope 34. Support plates 2 are installed on both the left and right sides above the detection device body 1, and a top plate 3 is installed above the support plates 2. The oil distributor assembly 5 is installed below the top plate 3 through the first electric telescopic rod 4. The circulating water pump 6 is installed on the right side of the right support plate 2. The water inlet pipe 7 and the water outlet pipe 8 are respectively installed above and below the circulating water pump 6. The detection liquid tank 9 is installed above the detection device body 1. The circulating water pump 6 conveys the liquid in the detection liquid tank 9. The water inlet pipe 7 is communicated with the inside of the detection liquid tank 9, and the water outlet pipe 8 is communicated with the inside of the oil distributor assembly 5. Moreover, the water outlet pipe 8 is designed as a telescopic structure. When the circulating water pump 6 is started, the circulating water pump 6 pumps out the liquid in the detection liquid tank 9 through the water inlet pipe 7, and then conveys the liquid to the oil distributor assembly 5 through the water outlet pipe 8. The oil distributor assembly 5 conveys the liquid to the fuel nozzle for the aeroengine fixed in the placement pipe 11 to detect the fuel nozzle for the aeroengine.

[0048] A connecting plate 10 is installed between the support plates 2, and a placement pipe 11 is installed on the connecting plate 10. Both the upper and lower ends of the placement pipe 11 are designed with an open structure. There are multiple placement pipes 11, and the number of positioning block assemblies 14 is equal to the number of placement pipes 11. Place the fuel nozzle of the aero-engine inside the placement pipe 11, and press the fuel nozzle downward to drive the sealing block 19 to move downward. At this time, the telescopic spring 18 is in a compressed state. Then start the second electric telescopic rod 12. The second electric telescopic rod 12 drives the movable bar 13 to move to the right. The movable bar 13 drives the positioning block assembly 14 to move to the right to clamp and fix the fuel nozzle in the placement pipe 11, thus facilitating the fixing of the fuel nozzle. The right side of the left support plate 2 is installed with a movable bar 13 through the second electric telescopic rod 12, and positioning block assemblies 14 are equidistantly installed on the movable bar 13. The positioning block assembly 14 is slidably connected to the placement pipe 11. The left side of the right support plate 2 is installed with a limiting block 21, and a limiting groove 22 is opened on the left side of the limiting block 21. The movable bar 13 is slidably connected to the limiting groove 22. When the positioning block assembly 14 moves to the right under force, the fixing of the fuel nozzle can be completed. When the movable bar 13 is under force, it can move left and right along the limiting groove 22 on the limiting block 21, so that the movable bar 13 is more stable when moving left and right. Through holes 15 are equidistantly opened on the movable bar 13, and damping rotating parts 16 are equidistantly installed on the movable bar 13. The damping rotating parts 16 are located at the upper right position of the through holes 15, and the positioning block assemblies 14 are located at the upper left position of the through holes 15. When the baffle 17 coincides with the through hole 15, the baffle 17 covers the through hole 15. The baffle 17 is subjected to anti-rust treatment. After the sealing performance detection of the fuel nozzle is completed, the baffle 17 can be driven to rotate through the damping rotating part 16. By pressing down the anti-sliding block 20, the baffle 17 can be rotated more easily, so that the through hole 15 covered by the baffle 17 is exposed. Moreover, the damping rotating part 16 is installed with the baffle 17, the upper part of the baffle 17 is installed with a sealing block 19 through a telescopic spring 18, and anti-sliding blocks 20 are installed on the left and right sides of the lower part of the sealing block 19. The shape of the sealing block 19 is designed according to the shape of the fuel nozzle to be detected. The elastic force of the telescopic spring 18 is less than the clamping force of the positioning block assembly 14 on the fuel nozzle when it is under force. Grooves are opened on the front surface of the anti-sliding block 20. The sealing block 19 seals the spraying end of the fuel nozzle under the action of the return spring force of the telescopic spring 18, thus facilitating the detection of the sealing performance of the fuel nozzle.

[0049] A hollow frame 23 is installed on the upper surface of the detection device body 1. A servo motor 24 is installed on the left side of the left support plate 2. The right side of the servo motor 24 is provided with a transmission shaft 25 through an output shaft. Fixed blocks 26 are installed on both the upper and lower sides of the transmission shaft 25. One ends of the fixed blocks 26 away from the transmission shaft 25 are both installed with measuring cylinders 28 through threaded connectors 27. The threaded connector 27 includes a threaded sleeve and a bolt. The threaded connector 27 is connected to the fixed block 26, the threaded sleeve is connected to the measuring cylinder 28, and the threaded sleeve and the bolt are in threaded connection. There are multiple measuring cylinders 28 and fixed blocks 26. The center line of the measuring cylinder 28 coincides with the center line of the through hole 15. The forward and reverse rotation of the servo motor 24 is controllable. A drainage pipe is communicated with the rear side of the hollow frame 23. After the flow rate of the fuel nozzle is detected, the servo motor 24 is started. The servo motor 24 drives the transmission shaft 25 to rotate through the output shaft. The transmission shaft 25 drives the measuring cylinder 28 to rotate by 90°. During the rotation of the liquid in the upper measuring cylinder 28, the liquid inside it can fall into the hollow frame 23 and be discharged through the drainage pipe in the hollow frame 23, which is convenient for cleaning the measuring cylinder 28. When in-depth cleaning of the measuring cylinder 28 is required, the upper measuring cylinder 28 is disassembled through the threaded connector 27, and then the transmission shaft 25 is driven by the servo motor 24 to rotate, exposing the lower measuring cylinder 28, so as not to affect the progress of the fuel nozzle flow rate detection.

[0050] A first bevel gear 29 is installed on the transmission shaft 25. A fixed shaft 30 is installed on the upper surface of the detection device body 1. A rotating shaft 31 is sleeved on the fixed shaft 30. The rotating shaft 31 is rotatably connected to the fixed shaft 30. The rotating shaft 31 and the fixed shaft 30 are located on the left side of the hollow frame 23. A second bevel gear 32 is installed at the upper end of the rotating shaft 31. The second bevel gear 32 is perpendicular to and meshes with the first bevel gear 29. When the rotating shaft 31 rotates, it can drive the first bevel gear 29 to rotate. The first bevel gear 29 drives the second bevel gear 32 to rotate. The second bevel gear 32 drives the rotating shaft 31 to rotate. A second bevel gear 32 is installed at the upper end of the rotating shaft 31. A connecting block 33 is installed on the right side of the left support plate 2. A winding rope 34 is installed on the connecting block 33. The end of the winding rope 34 is detachably connected to the rotating shaft 31. The length of the winding rope 34 is set according to actual use. When the rotating shaft 31 rotates, the rotating shaft 31 can wind up the winding rope 34. The number of uses of the measuring cylinder 28 can be estimated according to the winding situation of the winding rope 34, so as to facilitate in-depth cleaning of the measuring cylinder 28 in time and improve the service life of the measuring cylinder 28. After the in-depth cleaning of the measuring cylinder 28 is completed, the end of the winding rope 34 is detached from the rotating shaft 31 and reconnected.

[0051] Working principle: When using this fuel nozzle detection device for aero-engines, first, place the fuel nozzle of the aero-engine inside the placement tube 11, and press the fuel nozzle downward, driving the sealing block 19 to move downward. At this time, the telescopic spring 18 is in a compressed state. Then start the second electric telescopic rod 12. The second electric telescopic rod 12 drives the movable strip 13 to move to the right, and the movable strip 13 drives the positioning block assembly 14 to move to the right to clamp and fix the fuel nozzle in the placement tube 11, thus facilitating the fixation of the fuel nozzle. Then start the first electric telescopic rod 4. The first electric telescopic rod 4 drives the fuel distributor assembly 5 to move downward, making the fuel distributor assembly 5 close to the fuel nozzle. Start the circulating water pump 6. The circulating water pump 6 pumps out the liquid in the detection liquid tank 9 through the water inlet pipe 7, and then transports the liquid to the fuel distributor assembly 5 through the water outlet pipe 8. The fuel distributor assembly 5 transports the liquid into the fuel nozzle of the aero-engine fixed in the placement tube 11. If there is liquid in the baffle 17, it indicates that the sealing performance of the fuel nozzle is poor, so the sealing performance of the fuel nozzle can be detected.

[0052] After the sealing performance detection of the fuel nozzle is completed, the baffle 17 can be driven to rotate through the damping rotating part 16. By pressing down the anti-sliding block 20, it is easier to rotate the baffle 17, so that the through hole 15 covered by the baffle 17 is exposed. The liquid in the fuel nozzle can fall into the measuring cylinder 28 through the through hole 15, and the flow rate of the fuel nozzle can be detected through the measuring cylinder 28, so as to realize the detection of both the sealing performance and the flow rate of the fuel nozzle.

[0053] After the flow rate detection of the fuel nozzle is completed, start the servo motor 24. The servo motor 24 drives the transmission shaft 25 to rotate through the output shaft. The transmission shaft 25 drives the measuring cylinder 28 to rotate 90°. During the rotation of the liquid in the upper measuring cylinder 28, the liquid inside can fall into the hollow frame 23 and be discharged through the drainage pipe in the hollow frame 23, which is convenient for cleaning the measuring cylinder 28. When deep cleaning of the measuring cylinder 28 is required, remove the upper measuring cylinder 28 through the threaded connector 27, and then drive the transmission shaft 25 to rotate through the servo motor 24 to expose the lower measuring cylinder 28, so as not to affect the progress of the flow rate detection of the fuel nozzle.

[0054] When the rotating shaft 31 rotates, it can drive the first bevel gear 29 to rotate. The first bevel gear 29 drives the second bevel gear 32 to rotate, and the second bevel gear 32 drives the rotating shaft 31 to rotate. When the rotating shaft 31 rotates, the rotating shaft 31 can wind up the winding rope 34. The number of times the measuring cylinder 28 is used can be estimated according to the winding situation of the winding rope 34, so as to facilitate the timely deep cleaning of the measuring cylinder 28 and improve the service life of the measuring cylinder 28. After the deep cleaning of the measuring cylinder 28 is completed, the end of the winding rope 34 can be detached from the rotating shaft 31 and reconnected. Thus, a series of operations are completed. The content not described in detail in this specification belongs to the prior art well-known to those skilled in the art.

[0055] Although the present invention has been described in detail with reference to the foregoing embodiments, for those skilled in the art, they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A fuel nozzle testing device for an aircraft engine, comprising a testing device body (1), characterized in that: Support plates (2) are installed on both left and right sides of the detection device body (1), and a top plate (3) is installed above the support plate (2). An oil separator assembly (5) is installed below the top plate (3) via a first electric telescopic rod (4), and a circulating water pump (6) is installed on the right side of the right support plate (2); A connecting plate (10) is installed between the support plates (2), and a placement tube (11) is installed on the connecting plate (10); a movable bar (13) is installed on the right side of the left support plate (2) through a second electric telescopic rod (12), and a positioning block assembly (14) is equidistantly installed on the movable bar (13); through holes (15) are equidistantly opened on the movable bar (13), and a damping rotating member (16) is equidistantly installed on the movable bar (13), and a baffle (17) is installed on the damping rotating member (16); a sealing block (19) is installed above the baffle (17) through a telescopic spring (18), and anti-sliding blocks (20) are installed on both left and right sides of the sealing block (19); A hollow frame (23) is installed on the upper surface of the detection device body (1), a servo motor (24) is installed on the left side of the left support plate (2), and a transmission shaft (25) is installed on the right side of the servo motor (24) through an output shaft, and fixed blocks (26) are installed on both upper and lower sides of the transmission shaft (25), and a metering cylinder (28) is installed on the end of the fixed block (26) away from the transmission shaft (25) through a threaded connector (27); A first bevel gear (29) is mounted on the transmission shaft (25); a fixed shaft (30) is mounted on the upper surface of the detection device body (1); a rotating shaft (31) is sleeved on the fixed shaft (30); a second bevel gear (32) is mounted on the upper end of the rotating shaft (31); a connecting block (33) is mounted on the right side of a support plate (2) mounted on the left side; and a winding rope (34) is mounted on the connecting block (33).

2. The fuel nozzle detection device for an aircraft engine according to claim 1, characterized in that: A water inlet pipe (7) and a water outlet pipe (8) are respectively installed above and below the circulating water pump (6), and a detection liquid tank (9) is installed above the detection device body (1).

3. The fuel nozzle detection device for an aircraft engine according to claim 2, characterized in that: The water inlet pipe (7) is connected to the interior of the detection liquid box (9), the water outlet pipe (8) is connected to the interior of the oil separator assembly (5), and the water outlet pipe (8) is designed as a retractable structure.

4. The fuel nozzle detection device for an aircraft engine according to claim 1, characterized in that: The upper and lower ends of the placement tube (11) are both designed as open structures. A plurality of placement tubes (11) are provided, and the number of positioning block assemblies (14) is equal to the number of placement tubes (11).

5. The fuel nozzle detection device for an aircraft engine according to claim 1, characterized in that: The positioning block assembly (14) is slidably connected to the placement tube (11), a limiting block (21) is installed on the left side of the right support plate (2), and a limiting groove (22) is provided on the left side of the limiting block (21), and the movable bar (13) is slidably connected to the limiting groove (22).

6. The fuel nozzle detection device for an aircraft engine according to claim 1, characterized in that: The damping rotating member (16) is located on the right side above the through hole (15), the positioning block assembly (14) is located on the left side above the through hole (15), and when the baffle (17) overlaps with the through hole (15), the baffle (17) covers the through hole (15), and the baffle (17) is subjected to rust prevention treatment.

7. The fuel nozzle detection device for an aircraft engine according to claim 1, characterized in that: The shape of the sealing block (19) is designed according to the shape of the fuel nozzle to be detected, the elastic force of the telescopic spring (18) is smaller than the clamping force of the positioning block assembly (14) on the fuel nozzle when the positioning block assembly (14) is subjected to force, and a groove is provided on the front surface of the anti-sliding block (20).

8. The fuel nozzle detection device for an aircraft engine according to claim 1, characterized in that: The threaded connector (27) comprises a threaded sleeve and a bolt. The threaded connector (27) is connected to the fixed block (26). The threaded sleeve is connected to the metering cylinder (28). The threaded sleeve and the bolt are threadedly connected. The metering cylinder (28) and the fixed block (26) are both provided with a plurality of them. The center line of the metering cylinder (28) coincides with the center line of the through hole (15). The servo motor (24) is controllable in forward and reverse directions. The rear side of the hollow frame (23) is connected to a drainage pipe.

9. The fuel nozzle detection device for an aircraft engine according to claim 1, characterized in that: The rotating shaft (31) is rotatably connected to the fixed shaft (30). The rotating shaft (31) and the fixed shaft (30) are located on the left side of the hollow frame (23). A second bevel gear (32) is installed on the upper end of the rotating shaft (31). The second bevel gear (32) and the first bevel gear (29) are perpendicular to each other and mesh with each other.

10. The fuel nozzle detection device for aircraft engines according to claim 1, characterized in that: The end of the winding rope (34) is detachably connected to the rotating shaft (31), and the length of the winding rope (34) is set according to actual use.

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