CN211919035U

CN211919035U - Helicopter heat exchanger repair and inspection system

Info

Publication number: CN211919035U
Application number: CN202020477306.7U
Authority: CN
Inventors: 杨永生
Original assignee: Henan Tonglu Aviation Technology Co ltd
Current assignee: Henan Tonglu Aviation Technology Co ltd
Priority date: 2020-04-03
Filing date: 2020-04-03
Publication date: 2020-11-13
Anticipated expiration: 2030-04-03

Abstract

The utility model discloses a helicopter heat exchanger repair inspection system, the terminal of the ventilation pipe outside the inspection box both sides is fixed connection first detection mechanism and second detection mechanism respectively, set up the display, temperature sensor and pressure sensor on the outer wall in the shell homonymy of first detection mechanism respectively, utilize temperature sensor and pressure sensor to detect the temperature and the wind pressure of wind around passing through the heat exchanger, and transmit it to the display on the shell outer wall, compare the temperature and the wind pressure around on the display, effectively judge whether the heat exchange effect and the wind pressure of heat exchanger are normal, simple and fast, set up the silk mechanism that wafts at the lower extreme of the sealing top cap of inspection box, utilize mounting panel, rings and connecting piece to suspend the fiber silk bundle around the heat exchanger, in the airtight inspection box, when the leakproofness of heat exchanger appears leaking, the fiber silk bundle can appear swinging and display, whether the tightness of the heat exchanger is qualified or not is detected through whether the fiber tows swing or not, and the method is simple, convenient and low in cost.

Description

Helicopter heat exchanger repair and inspection system

Technical Field

The utility model relates to a maintenance system technical field specifically is a helicopter heat exchanger repairs inspection system.

Background

Air conditioning heat exchangers, which are important components for controlling the pressure, flow rate, temperature, humidity and flow direction of compressed air, are used in modern aircraft primarily in environmental control systems and air supply systems. The prior air conditioning heat exchanger on an airplane is mainly a plate-fin heat exchanger. Most of the heat exchanger baffles and fins are made of very thin aluminum plates, the thickness of the baffles is generally 1-2mm, and the thinnest is 0.36 mm; the thickness of the fins is generally 0.3-2 mm. The fluid containing corrosive particles is easy to corrode aluminum, and internal leakage is easy to exceed the standard. Stress and mechanical stress generated by cold-heat exchange easily cause structural damage, cause external leakage exceeding the standard, and can cause the damage of the whole heat exchanger in serious conditions. Heat exchangers that have been in operation for some time often require major repairs to ensure proper operation of the aircraft system.

However, the major repair technology is technically blocked by the equipment manufacturers in foreign factories at present, and no information about the major repair technology and the equipment is available on the part repair handbooks. The maintenance inspection of the heat exchanger is not easy to implement, the maintenance inspection can not be judged whether to be qualified or not, and the heat exchanger is sent to a foreign original factory to be maintained, so that the cost is high, and the time is long. Therefore, we propose a helicopter heat exchanger repair and inspection system.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a helicopter heat exchanger repairs inspection system sets up respectively on the seal cap lower extreme of inspection case and inspection case bottom plate and wafts silk mechanism and damper, utilizes the ventilation pipe to connect first detection mechanism and second detection mechanism respectively on the both sides outer wall of inspection case to and keep away from the play dryer of intercommunication air-blower on the outer wall of ventilation pipe one side at second detection mechanism, thereby solved the problem that proposes in the above-mentioned background.

In order to achieve the above object, the utility model provides a following technical scheme: a helicopter heat exchanger repair and inspection system comprises a support plate and an inspection device, wherein the inspection device is installed at the upper end of the support plate and comprises a sealing top cover, a floating wire mechanism, an inspection box, a damping mechanism, an observation window, a ventilation pipe, a first detection mechanism, a second detection mechanism and an air blower, the floating wire mechanism is arranged at the bottom of the sealing top cover, the sealing top cover is sealed and covered at the top of the inspection box, the damping mechanism is installed at the upper end of a bottom plate in the inspection box, the observation window is arranged on the outer wall of the front side of the inspection box, the ventilation pipe is respectively arranged on the outer walls of the two sides of the inspection box, the ventilation pipe is clamped and embedded in the side wall of the inspection box, one end of the ventilation pipe extends to the inside of the inspection box, the other end of the ventilation pipe extends to the outside of the inspection box, the tail ends of the outside of the two sides of the inspection box are respectively and fixedly connected with the first, an air outlet cylinder of the air blower is communicated with the outer wall of one side, far away from the ventilation pipe, of the second detection mechanism.

Further, the silk mechanism that wafts includes mounting panel, rings, connecting piece and fibre silk bundle, and mounting panel fixed connection is in seal cap's bottom, and the lower extreme border punishment of mounting panel evenly is provided with rings respectively, and the connecting piece has all been bound to the lower extreme of rings, and the bottom of connecting piece all is provided with the fibre silk bundle.

Further, flanges are respectively arranged at the tail ends of the ventilation pipes inside two sides of the inspection box.

Further, damper includes casing, damping spring group, fly leaf, movable block and bearing plate, and the cavity has been seted up to the inside of casing, and damping spring group is installed to the bottom plate upper end of cavity, and the top fixed connection fly leaf of damping spring group, the upper end of fly leaf are provided with the movable block, and the top of movable block runs through the top of casing and upwards extends to its outside, the upper end fixed connection bearing plate of movable block.

Furthermore, the upper end of the bearing plate is provided with an elastic rubber pad.

Furthermore, transparent toughened glass is embedded between the inner walls of the observation windows, and the edge joints of the transparent toughened glass are sealed.

Furthermore, the first detection mechanism comprises a shell, a display, a temperature sensor and a pressure sensor, the display is arranged on the outer wall of the front face of the shell, the temperature sensor and the pressure sensor are respectively arranged on the inner wall of the shell on the same side of the display, and the temperature sensor and the pressure sensor are electrically connected with the display.

Further, the structural composition of the first detection mechanism is consistent with that of the second detection mechanism.

Compared with the prior art, the beneficial effects of the utility model are as follows:

1. the utility model provides a pair of inspection system is repaired to helicopter heat exchanger, at the outside ventilation pipe end difference fixed connection first detection mechanism of inspection case both sides and second detection mechanism, set up the display respectively on the shell homonymy inside and outside wall of first detection mechanism, temperature sensor and pressure sensor, utilize temperature sensor and pressure sensor to detect temperature and the wind pressure through wind around the heat exchanger, and transmit the display on the shell outer wall with it, temperature and wind pressure around on the contrast display, effectively judge whether heat exchanger's heat transfer effect and wind pressure are normal, it is simple quick.

2. The utility model provides a pair of inspection system is repaired to helicopter heat exchanger sets up the silk mechanism that wafts at the seal cap lower extreme of inspection case, utilizes mounting panel, rings and connecting piece with the fibre silk bundle suspension around heat exchanger, in inclosed inspection case, when heat exchanger's leakproofness is not enough to appear leaking, the fibre silk bundle can appear swinging the video picture, whether swing through the fibre silk bundle detects heat exchanger's leakproofness qualified, simple convenient with low costs.

3. The utility model provides a pair of inspection system is repaired to helicopter heat exchanger installs damper in the bottom plate upper end of inspection incasement, sets up damping spring group in casing cavity's bottom plate upper end, and damping spring group passes through the bearing plate of fly leaf and movable block connecting band elastic rubber pad, alleviates the vibrations when heat exchanger places through damping spring group and elastic rubber pad, avoids taking place between heat exchanger and the bearing plate violent collision and leads to the internals impaired.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic structural view of the filament-floating mechanism of the present invention;

FIG. 3 is a schematic structural view of the damping mechanism of the present invention;

fig. 4 is a schematic structural diagram of the first detecting mechanism of the present invention.

In the figure: 1. a support plate; 2. a testing device; 21. sealing the top cover; 22. a filament floating mechanism; 221. mounting a plate; 222. a hoisting ring; 223. a connecting member; 224. a fiber tow; 23. a checking box; 24. a damping mechanism; 241. a housing; 242. a damping spring set; 243. a movable plate; 244. a movable block; 245. a bearing plate; 246. an elastic rubber pad; 25. an observation window; 26. a vent pipe; 27. a first detection mechanism; 271. a housing; 272. a display; 273. a temperature sensor; 274. a pressure sensor; 28. a second detection mechanism; 29. a blower.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1, a helicopter heat exchanger repair and inspection system comprises a support plate 1 and an inspection device 2, wherein the inspection device 2 is installed at the upper end of the support plate 1, the inspection device 2 comprises a sealing top cover 21, a flying wire mechanism 22, an inspection box 23, a damping mechanism 24, an observation window 25, a ventilation pipe 26, a first detection mechanism 27, a second detection mechanism 28 and an air blower 29, the flying wire mechanism 22 is arranged at the bottom of the sealing top cover 21, the sealing top cover 21 is sealed and covered at the top of the inspection box 23, the damping mechanism 24 is installed at the upper end of a bottom plate in the inspection box 23, the observation window 25 is arranged on the outer wall of the front side of the inspection box 23, transparent toughened glass is embedded between the inner walls of the observation window 25, the edges of the transparent toughened glass are sealed, the observation window 25 is arranged to facilitate the observation of the conditions in the inspection box 23, the ventilation pipes 26 are respectively arranged on the outer walls of the two sides of the inspection, ventilation pipe 26 inlay card is in the lateral wall of inspection case 23, one end extends to the inside of inspection case 23, the other end extends to the outside of inspection case 23, and the inside ventilation pipe 26 end in inspection case 23 both sides is provided with flange 210 respectively, the outside ventilation pipe 26 end in inspection case 23 both sides is the first detection mechanism 27 of fixedly connected with and second detection mechanism 28 respectively, be provided with out the tuber pipe on the outer wall of ventilation pipe 26 one side is kept away from to first detection mechanism 27, the play dryer of air-blower 29 is linked together with the outer wall that ventilation pipe 26 one side was kept away from to second detection mechanism 28, be connected the tuber pipe at ventilation pipe 26 and heat exchanger both ends and install in inspection case 23 through flange 210, start each equipment in inspection case 23 both sides and can inspect.

Referring to fig. 2, in a repairing and inspecting system for a helicopter heat exchanger, a flying wire mechanism 22 includes an installation plate 221, hanging rings 222, connecting pieces 223 and fiber tows 224, the installation plate 221 is fixedly connected to the bottom of a sealing top cover 21, the hanging rings 222 are respectively and uniformly arranged at the lower end edges of the installation plate 221, the connecting pieces 223 are all bound at the lower ends of the hanging rings 222, the fiber tows 224 are all arranged at the bottom of the connecting pieces 223, the fiber tows 224 are suspended around the heat exchanger, when leakage occurs due to insufficient sealing performance of the heat exchanger in a closed environment, swinging imaging of the fiber tows 224 occurs, whether the sealing performance of the heat exchanger is qualified is detected by whether the fiber tows 224 swing, and the system is simple, convenient and.

Referring to fig. 3, a helicopter heat exchanger repair and inspection system, a damping mechanism 24 includes a housing 241, a damping spring set 242, a movable plate 243, a movable block 244 and a bearing plate 245, a cavity is formed in the housing 241, the damping spring set 242 is installed at the upper end of the bottom plate of the cavity, the top of the damping spring set 242 is fixedly connected to the movable plate 243, the movable block 244 is disposed at the upper end of the movable plate 243, the top of the movable block 244 penetrates through the top of the housing 241 and extends upwards to the outside of the housing, the upper end of the movable block 244 is fixedly connected to the bearing plate 245, an elastic rubber pad 246 is disposed at the upper end of the bearing plate 245, and the vibration generated when the heat exchanger is placed is reduced through the damping spring set 242 and the elastic rubber pad 246, so that damage to internal parts.

Referring to fig. 4, a helicopter heat exchanger repair and inspection system, the structural composition of a first detection mechanism 27 is consistent with that of a second detection mechanism 28, the first detection mechanism 27 includes a housing 271, a display 272, a temperature sensor 273 and a pressure sensor 274, the display 272 is disposed on the outer wall of the front face of the housing 271, the temperature sensor 273 and the pressure sensor 274 are disposed on the inner wall of the housing 271 on the same side of the display 272, the temperature sensor 273 and the pressure sensor 274 are electrically connected to the display 272, the temperature and the pressure of front and rear wind passing through the heat exchanger are detected by the temperature sensor 273 and the pressure sensor 274 and transmitted to the display 272 on the outer wall of the housing 271, and the front and rear temperature and the wind pressure on the display 272 are compared to effectively judge whether the heat exchange effect and the wind pressure of the heat exchanger are normal.

In summary, the following steps: the utility model provides a helicopter heat exchanger repairs checkout system, at the outside ventilation pipe 26 end fixed connection first detection mechanism 27 and second detection mechanism 28 respectively of inspection box 23 both sides, set up display 272 on the shell 271 of first detection mechanism 27 homonymy inside and outside wall respectively, temperature sensor 273 and pressure sensor 274, utilize temperature sensor 273 and pressure sensor 274 to detect the temperature and the wind pressure of wind around passing through the heat exchanger, and transmit it to display 272 on the shell 271 outer wall, compare temperature and wind pressure around on the display 272, effectively judge whether heat exchanger's heat transfer effect and wind pressure are normal, it is simple quick; the lower end of a sealing top cover 21 of the inspection box 23 is provided with the floating wire mechanism 22, the fiber tows 224 are suspended around the heat exchanger by using the mounting plate 221, the hanging ring 222 and the connecting piece 223, when the heat exchanger is insufficient in sealing performance and leaks in the sealed inspection box 23, the fiber tows 224 can swing and display, whether the sealing performance of the heat exchanger is qualified or not is detected by whether the fiber tows 224 swing or not, and the method is simple, convenient and low in cost; the damping mechanism 24 is installed at the upper end of the bottom plate in the inspection box 23, the damping spring group 242 is arranged at the upper end of the bottom plate of the cavity of the shell 241, the damping spring group 242 is connected with the bearing plate 245 with the elastic rubber pad 246 through the movable plate 243 and the movable block 244, the vibration generated when the heat exchanger is placed is relieved through the damping spring group 242 and the elastic rubber pad 246, and damage to internal parts caused by violent collision between the heat exchanger and the bearing plate 245 is avoided. This helicopter heat exchanger repairs inspection system, simple structure, convenient and practical, convenient operation.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a helicopter heat exchanger repairs checkout system, includes backup pad (1) and verifying attachment (2), and verifying attachment (2) are installed to the upper end of backup pad (1), its characterized in that: verifying attachment (2) is including sealing top cap (21), flying wire mechanism (22), inspection box (23), damper (24), observation window (25), ventilation pipe (26), first detection mechanism (27), second detection mechanism (28) and air-blower (29), the bottom of sealing top cap (21) is provided with flying wire mechanism (22), and sealing top cap (21) closing cap is in the top of inspection box (23), damper (24) are installed to the bottom plate upper end in inspection box (23), observation window (25) set up on the front outer wall of inspection box (23), and be provided with ventilation pipe (26) on the both sides outer wall of inspection box (23) respectively, ventilation pipe (26) inlay card is in the lateral wall of inspection box (23), one end extends to the inside of inspection box (23), the other end extends to the outside of inspection box (23), the terminal fixedly connected with first detection mechanism (27) and second detection mechanism (26) respectively of ventilation pipe (26) of inspection box (23) both sides outside 28) An air outlet pipe is arranged on the outer wall of one side, away from the ventilation pipe (26), of the first detection mechanism (27), and an air outlet cylinder of the air blower (29) is communicated with the outer wall of one side, away from the ventilation pipe (26), of the second detection mechanism (28).

2. A helicopter heat exchanger repair inspection system according to claim 1, wherein: the floating wire mechanism (22) comprises a mounting plate (221), lifting rings (222), connecting pieces (223) and fiber tows (224), the mounting plate (221) is fixedly connected to the bottom of the sealing top cover (21), the lifting rings (222) are evenly arranged at the edge of the lower end of the mounting plate (221) respectively, the connecting pieces (223) are bound to the lower ends of the lifting rings (222), and the fiber tows (224) are arranged at the bottom of the connecting pieces (223).

3. A helicopter heat exchanger repair inspection system according to claim 1, wherein: flanges (210) are respectively arranged at the tail ends of the ventilation pipes (26) in the two sides of the inspection box (23).

4. A helicopter heat exchanger repair inspection system according to claim 1, wherein: damper (24) are including casing (241), damping spring group (242), fly leaf (243), movable block (244) and bearing plate (245), the cavity has been seted up to the inside of casing (241), damping spring group (242) are installed to the bottom plate upper end of cavity, top fixed connection fly leaf (243) of damping spring group (242), the upper end of fly leaf (243) is provided with movable block (244), the top of movable block (244) runs through the top of casing (241) and upwards extends to its outside, the upper end fixed connection bearing plate (245) of movable block (244).

5. A helicopter heat exchanger repair inspection system according to claim 4, wherein: the upper end of the bearing plate (245) is provided with an elastic rubber pad (246).

6. A helicopter heat exchanger repair inspection system according to claim 1, wherein: transparent toughened glass is inlaid between the inner walls of the observation windows (25), and the edge joints of the transparent toughened glass are sealed.

7. A helicopter heat exchanger repair inspection system according to claim 1, wherein: the first detection mechanism (27) comprises a shell (271), a display (272), a temperature sensor (273) and a pressure sensor (274), the display (272) is arranged on the outer wall of the front face of the shell (271), the temperature sensor (273) and the pressure sensor (274) are respectively arranged on the inner wall of the shell (271) on the same side of the display (272), and the temperature sensor (273) and the pressure sensor (274) are electrically connected with the display (272).

8. A helicopter heat exchanger repair inspection system according to claim 7, wherein: the structural composition of the first detection mechanism (27) is consistent with that of the second detection mechanism (28).