CN116213340A - Tool and equipment for cleaning low-pressure air inlet on wing of aero-engine - Google Patents
Tool and equipment for cleaning low-pressure air inlet on wing of aero-engine Download PDFInfo
- Publication number
- CN116213340A CN116213340A CN202211701112.0A CN202211701112A CN116213340A CN 116213340 A CN116213340 A CN 116213340A CN 202211701112 A CN202211701112 A CN 202211701112A CN 116213340 A CN116213340 A CN 116213340A
- Authority
- CN
- China
- Prior art keywords
- wing
- mounting
- joint
- spray
- spray pipe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/02—Cleaning by the force of jets or sprays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/04—Cleaning involving contact with liquid
- B08B3/08—Cleaning involving contact with liquid the liquid having chemical or dissolving effect
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B77/00—Component parts, details or accessories, not otherwise provided for
- F02B77/04—Cleaning of, preventing corrosion or erosion in, or preventing unwanted deposits in, combustion engines
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cleaning Of Streets, Tracks, Or Beaches (AREA)
Abstract
The invention provides a tool and equipment for cleaning a low-pressure air inlet on a wing of an aeroengine, which aims to solve the technical problem that a great amount of dust and carbon deposit can adhere to an air flow channel and a blade of the engine under the influence of the environment and influence the performance of the engine. The mounting point is unique when the invention is used, so that the invention can be accurately positioned; the length of the jet section of the jet pipe can fully cover the low-pressure air inlet, so that the jet angle and the jet distance can be ensured, and the air inlet channel can be fully covered; the spray pipes and the spray holes on the spray pipes are uniformly distributed, so that the spray is uniform; the wing cleaning device has the advantages that the structure is simple and compact, the wing cleaning device can be used in a scene with a narrow wing state space, the wing cleaning device can be quickly and accurately connected with an engine and a cleaning device, and the direction of an injection hole on the installation and adjustment spray pipe is convenient and quick, so that the wing cleaning device can clean the wing in time, and the purpose of high-efficiency cleaning of the low-pressure air inlet hole of the engine is achieved.
Description
Technical Field
The invention relates to the field of aviation maintenance and guarantee, in particular to a low-pressure air inlet cleaning tool and equipment for an aero-engine.
Background
In the field of aviation maintenance and guarantee, as the low-pressure air inlet of the aeroengine is influenced by the environment after the aeroengine flies for a period of time, a large amount of dust and carbon deposit can adhere to the low-pressure air inlet of the aeroengine to influence the performance of the aeroengine, the aeroengine needs to be returned to a factory for repair in advance before reaching a major repair period, and the use of equipment is seriously influenced. The inventor of the invention discovers through long-term maintenance test experience that if the low-pressure air inlet of the engine can be cleaned in time, the performance and the service life of the engine can be improved. However, the existing cleaning equipment is used for cleaning the low-pressure air inlet of the engine, the engine is required to be separated from the aircraft, and the engine is placed on a special test bed and is debugged into an engine test state, so that the engine can be cleaned, the cleaning efficiency is low, and the workload is high.
Disclosure of Invention
In order to solve the technical problems that an engine airflow channel and a blade are affected by the environment and a large amount of dust and carbon deposit can adhere to the airflow channel and the blade to affect the performance of the engine, the invention provides a tool and equipment for cleaning a low-pressure air inlet of an aeroengine on a wing, which are simple to operate and convenient to use.
The technical scheme of the invention is as follows:
the utility model provides an aeroengine low pressure inlet is at wing washs frock which characterized in that: the device comprises a mounting shaft, a connector mounting seat, a connector, a compression nut and a spray pipe assembly;
one end of the mounting shaft is in threaded connection with the mounting hole of the bonnet hood, a cleaning agent flow passage is formed in the other end of the mounting shaft from the shaft end to the middle along the axial direction, a plurality of flow dividing holes communicated with the cleaning agent flow passage are formed in the side wall of the mounting shaft along the circumferential direction, a limiting step for limiting the axial direction of the joint mounting seat and two ring grooves for mounting sealing rings are further formed in the side wall of the mounting shaft, and the two ring grooves are respectively located on two sides of the flow dividing holes;
the joint mounting seat and the compression nut are sequentially mounted on the mounting shaft, the joint mounting seat is axially fixed through the limiting step and the compression nut, the diversion hole is positioned in a cavity formed by the joint mounting seat and the mounting shaft, and sealing between the joint mounting seat and the mounting shaft is realized by mounting a sealing ring in the annular groove;
the number of the connectors is N, the connectors are uniformly distributed and welded on the connector mounting seat along the circumferential direction and are communicated with the inner cavity of the connector mounting seat, and then the connectors are communicated with the diversion holes after being assembled; n is more than or equal to 3;
the spray pipe assembly comprises a spray pipe, a sleeve nut, a nozzle, a fixed block and a plug; the spray pipe comprises an inlet section and a spray section which are connected in sequence, wherein the inlet section is detachably connected and communicated with the joint, and a plurality of spray holes are uniformly distributed on the side wall of the spray section; the length of the injection section is matched with the length of the low-pressure air inlet, so that the injection hole can fully cover the low-pressure air inlet; the outer sleeve nut and the nozzle are sleeved on the inlet section of the spray pipe, and the outer sleeve nut is positioned outside the nozzle; the fixed block is sleeved and welded outside the spray pipe; the outer surface of the fixed block is the fixed position of the wrench when the spray pipe is installed; the plug is inserted into and welded to the end of the jet section of the jet pipe.
Further, an inclined plane is processed on the outer side wall of the plug to form a milling structure, and the direction of the milling structure is consistent with the injection direction of the injection hole on the injection pipe.
Further, at least three of the diversion holes are provided.
Further, the whole connector mounting seat is of a hexahedral structure, and one surface is provided with a shaft hole penetrating from the surface to the opposite surface, and the shaft hole is used for being matched with the mounting shaft; the other four surfaces of the joint mounting seat are respectively provided with a joint mounting hole for mounting the joint, and the joint mounting holes are step holes;
the number of the connectors is four, and the connectors are respectively arranged in the connector mounting holes.
Further, the joint and the jet pipe butt joint form an aviation 74-degree flaring sealing structure.
Further, the cleaning agent flow passage further comprises a dust cap arranged on the mounting shaft, wherein the dust cap is used for sealing a port of the cleaning agent flow passage in a non-use state.
The invention also provides a cleaning device for the low-pressure air inlet of the aero-engine on-wing, which comprises a cleaning device; the special feature is that: the low-pressure air inlet on-wing cleaning tool of the aero-engine is further included; the cleaning device is connected with a mounting shaft in the wing cleaning tool, and cleaning agent is fed into a cleaning agent flow passage of the mounting shaft.
The invention has the beneficial effects that:
1. the invention has simple and compact structure, can be used in the scene with narrow wing state space, can be quickly and accurately connected with an engine and a cleaning device, and is convenient and quick to install and adjust the direction of the spray hole on the spray pipe, so that the purpose of cleaning the wing can be realized, the purpose of cleaning the low-pressure air inlet hole of the engine in time and high efficiency can be realized, and the performance and the reliable work of the engine can be ensured. In the wing cleaning, the engine is not detached from the aircraft, but the engine is mounted on the aircraft.
2. The mounting point is unique (only can be arranged at the mounting hole of the bonnet cover) when the bonnet cover is used, so that the bonnet cover can be accurately positioned; the length of the jet section of the jet pipe can fully cover the low-pressure air inlet, so that the jet angle and the jet distance can be ensured, and the air inlet channel can be fully covered; the spray pipes and the spray holes on the spray pipes are uniformly distributed, so that the spray is uniform; therefore, the invention can greatly improve the cleaning effect and efficiency.
3. The invention can realize the cleaning of the engine in the wing state and the cleaning of the engine in the non-wing state; the non-wing state refers to a state in which the engine is separated from the aircraft by washing, placed on a dedicated test bed, and debugged into an engine test state.
Drawings
Fig. 1 is a perspective view of the wing cleaning tool of the present invention.
Fig. 2 is a partial enlarged view at a in fig. 1.
Fig. 3 is a partial enlarged view at B in fig. 1.
Fig. 4 is a front view of the wing cleaning tool of the present invention.
Fig. 5 is a left side view (half cross-sectional view) of the present invention in a wing cleaning tool.
Fig. 6 is a schematic structural view of a joint mount in a wing cleaning tool according to the present invention, wherein: (a) is a perspective view, and (b) is an axial sectional view.
Fig. 7 is a schematic structural view of the installation shaft in the wing cleaning tool according to the present invention, wherein: (a) is a perspective view, (b) is an axial sectional view, and (c) is a sectional view taken along the direction A-A in (b).
Fig. 8 is a schematic structural view of a joint in a wing cleaning tool according to the present invention, wherein: (a) is a perspective view, and (b) is an axial sectional view.
Fig. 9 is a perspective view of the press nut of the present invention in a wing cleaning tool.
Fig. 10 is a schematic structural view of the dust cap in the wing cleaning tool according to the present invention, wherein: (a) is a perspective view, and (b) is an axial sectional view.
FIG. 11 is a schematic structural view of the nozzle of the present invention in a wing cleaning tool.
Fig. 12 is a schematic structural view of a plug in a wing cleaning tool according to the present invention, wherein: (a) is a perspective view, (b) is a front view, and (c) is a left view.
Fig. 13 is a schematic structural view of the coat nut in the wing cleaning tool according to the invention, wherein: (a) is a perspective view, (b) is an axial sectional view, and (c) is a left side view.
Fig. 14 is a schematic structural view of a nozzle in the wing cleaning tool according to the present invention, wherein: (a) is a perspective view, (b) is an axial sectional view, and (c) is a left side view.
Fig. 15 is a schematic structural view of a fixing block in the wing cleaning tool according to the present invention, wherein: (a) is a perspective view, (b) is an axial sectional view, and (c) is a left side view.
FIG. 16 is a schematic illustration of the mating relationship between the fitting, nipple, jacketing nut and spout of the present invention.
Reference numerals:
1-a joint mounting base; 101-a joint mounting hole; 102-shaft hole;
2-mounting a shaft; 201-first threads; 202-a second thread; 203-ring grooves; 204-limiting steps; 205-a cleaning agent flow channel; 206-a diversion aperture;
3-linker; 301-through holes; 302-conical surface; 303-external threads;
4-compressing the nut; 5-a sealing ring; 6-a dust cap;
7-spraying pipes; 701-injection hole;
8-plugs; 801—small diameter section; 802-large diameter section; 803-milling a flat structure;
9-sheathing the nut; 10-a nozzle; 11-fixed block.
Detailed Description
The engine airflow channel is the airflow channel from the engine air inlet to the engine tail nozzle, the low-pressure air inlet is the engine low-pressure compressor airflow channel, and the long-term repair test summary shows that: the low-pressure air inlet of the engine is cleaned, so that the performance of the engine can be effectively improved, and the service life of the engine is ensured. Therefore, the invention provides a tool and equipment for cleaning a low-pressure air inlet of an aeroengine on a wing. Before cleaning, only the engine hood is required to be disassembled, and the cleaning tool is integrally installed on the engine by utilizing the engine hood installation bolt holes.
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1-16, the low-pressure air inlet in-wing cleaning tool for the aeroengine comprises a joint mounting seat 1, a mounting shaft 2, a joint 3, a compression nut 4, a sealing ring 5, a dust cap 6, a spray pipe 7, a plug 8, an outer sleeve nut 9, a nozzle 10 and a fixing block 11.
As shown in fig. 6, the joint mounting seat 1 has a hexahedral structure as a whole, and one surface is provided with a shaft hole 102 penetrating from the surface to the opposite surface thereof, and the shaft hole 102 is used for being matched with the mounting shaft 2; the other four surfaces are provided with a joint mounting hole 101 for mounting the joint 3, and the joint mounting hole 101 is a step hole.
As shown in fig. 8, the outer wall of the joint 3 is provided with a step positioning surface matched with the joint mounting hole 101, the middle part of the end surface of the joint 3 is provided with a through hole 301 along the axial direction, and the through hole 301 is used for mounting a spray pipe assembly; the end part of the joint 3 for being butted with the spray pipe 7 is provided with a conical surface 302 matched with the flaring of the inlet section of the spray pipe 7, and the conical surface 302 and the flaring of the inlet section of the spray pipe 7 are matched to form an aviation 74-degree flaring sealing structure; the outer side wall of the joint 3 is also provided with external threads 303 which are used for being matched and connected with the internal threads of the coat nut 9; in the embodiment, the number of the joints 3 is 4, and the joints are respectively arranged at the 4 joint mounting holes 101 on the joint mounting seat 1 and are welded with the joint mounting holes to jointly form a spray pipe mounting seat; since each connector 3 is capable of connecting one nozzle assembly, the nozzle mount of the present embodiment can mount 4 nozzle assemblies.
The single spray pipe assembly comprises a spray pipe 7, a jacket nut 9, a nozzle 10, a fixed block 11 and a plug 8; the spray pipe 7 comprises an inlet section and a spray section which are connected in sequence; the inlet section is used for being detachably connected with the joint 3; the inlet section is designed into a flaring structure and is used for being matched with a conical surface at the end part of the joint 3 to form an aviation 74-degree flaring sealing structure; a plurality of injection holes 701 are uniformly distributed on the side wall of the injection section; the length of the injection section is matched with the length of the low-pressure air inlet, so that the injection hole 701 can fully cover the low-pressure air inlet to ensure the injection angle and distance; the coat nut 9, the nozzle 10, the fixed block 11 and the plug 8 are sequentially arranged on the spray pipe 7; the outer sleeve nut 9 and the nozzle 10 are sleeved on the inlet section of the spray pipe 7, the outer sleeve nut 9 is sleeved outside the nozzle 10, the outer sleeve nut 9 and the nozzle 10 are manufactured according to aviation connector standards, when the outer sleeve nut 9 is screwed, the flaring of the spray pipe 7 and the conical surface of the connector 3 can be compressed through the nozzle 10, and the sealing connection between the connector 3 and the spray pipe 7 is realized; the fixed block 11 is sleeved and welded outside the spray pipe 7, and the outer surface of the fixed block 11 is the fixed position of a wrench when the spray pipe 7 is installed; the plug 8 is inserted into and welded at the end part of the spraying section of the spray pipe 7; as shown in fig. 12, the plug 8 is a stepped shaft, the small diameter section 801 of the stepped shaft is used for being mounted in cooperation with the inner diameter of the spray pipe 7, the outer side wall of the cylinder of the large diameter section 802 is processed with inclined planes symmetrical relative to the axis to form a milling flat structure 803, and during mounting, attention should be paid to the angular relationship between the milling flat structure 803 on the side wall of the plug 8 and the spray hole 701 on the spray pipe 7, namely, during mounting, the direction of the milling flat structure 803 of the plug 8 is consistent with the spray direction of the spray hole on the spray pipe 7, so that the spray direction of the spray pipe 7 can be judged through the direction of the milling flat structure 803 of the plug 8.
As shown in fig. 7, one end of the mounting shaft 2 is provided with a first screw 201 for screw-coupling with the bonnet mounting hole; the other end of the mounting shaft 2 is provided with a second thread 202 for being in threaded connection with the compression nut 4 and the dust cap 6; the side wall of the mounting shaft 2 is also provided with two ring grooves 203 for mounting sealing rings; the middle part of the side wall of the mounting shaft 2 is also provided with a limiting step 204 for limiting the axial position of the joint mounting seat 1; a cleaning agent flow passage 205 is axially formed from the end to the middle at one end of the installation shaft 2 having the second thread 202, four diversion holes 206 communicated with the cleaning agent flow passage 205 are respectively formed on the side wall of the middle of the installation shaft 2 along the radial direction, and the four diversion holes 206 are respectively positioned between the two ring grooves 203.
The working principle and the using method of the invention are as follows:
firstly, a sealing ring 5 is arranged in a ring groove 203 on the side wall of a mounting shaft 2, one end of the mounting shaft 2 provided with the sealing ring 5 is screwed into an engine bonnet mounting hole and screwed, a joint mounting seat 1 is arranged on the mounting shaft 2 from the other end of the mounting shaft 2, at the moment, four flow dividing holes 206 on the mounting shaft 5 are all positioned in the joint mounting seat 1, and the sealing of two ends of the matching surface of the joint mounting seat 1 and the mounting shaft 5 can be realized through the sealing ring 5;
then, the joint mounting seat 1 is rotated along the circumferential direction of the mounting shaft 2 to adjust the positions of the 4 joints 3 thereon to be directed to meet the requirements (namely, to meet the condition that the spray holes on the spray pipe assembly mounted on the spray pipe assembly can face the engine), and the compression nut 4 is installed outside the mounting shaft 2 to compress the joint mounting seat 1;
then, the 4 spray pipe assemblies are respectively arranged on the 4 joints 3, the spray pipes 7 in the spray pipe assemblies are adjusted to adjust the direction of the spray holes 701 on the spray pipe assemblies, after the adjustment, the outer nuts 9 on the spray pipes 7 are screwed down to ensure the sealing of the joints 3 (the sealing structure formed by the conical end parts of the joints 3 and the flaring of the spray pipes 7 is an aviation 74-degree flaring sealing structure, and the sealing of the joints 3 can be ensured by screwing down the nuts 9);
finally, the hose connector of the existing cleaning device is connected to the cleaning agent flow passage 205 at the end of the installation shaft 2 and is screwed.
During cleaning, cleaning solution enters the cleaning agent flow channel 205 of the mounting shaft 2 through a hose of the cleaning device, then enters the joint mounting seat 1 through four flow dividing holes 206 communicated with the cleaning agent flow channel 205 on the mounting shaft 2, then enters the joint 3, and finally is uniformly sprayed into an engine airflow channel through the spray hole 701 of the spray pipe 7.
After the cleaning, if the cleaning tool of the present invention is not used for a long time, the dust cap 6 can be mounted on the end of the mounting shaft 2 having the cleaning agent flow path 205, so that foreign matters such as dust can be prevented from entering the mounting shaft 2.
The invention has been described above using only 4 nozzle assemblies mounted on a nozzle mount. Because the engine compressor is rotating, in other embodiments, the number of the nozzle assemblies can be specifically adjusted according to the required cleaning flow, and correspondingly, the structural form of the nozzle mounting seat and the number of the connectors 3 should be adaptively adjusted, so that the nozzle assemblies can be uniformly sprayed within the rotation radius range of the engine compressor, and the pressure and the flushing flow can be ensured.
In addition, in other embodiments, the connector 3 and the nozzle 7 can also adopt a quick-assembling sealing connection structure in other structural forms, and the above description only uses an aviation 74-degree flaring sealing structure as an example.
In addition, the invention also provides a low-pressure air inlet on-wing cleaning device of the aeroengine, which comprises the cleaning tool and a cleaning device connected with the cleaning tool for matching, wherein the cleaning device is an existing mature product and is used for feeding cleaning solution into a spray pipe 7 in the cleaning tool through a dust cap 6.
Claims (7)
1. The utility model provides an aeroengine low pressure inlet is at wing washs frock which characterized in that: the device comprises a mounting shaft, a connector mounting seat, a connector, a compression nut and a spray pipe assembly;
one end of the mounting shaft is in threaded connection with the mounting hole of the bonnet hood, a cleaning agent flow passage is formed in the other end of the mounting shaft from the shaft end to the middle along the axial direction, a plurality of flow dividing holes communicated with the cleaning agent flow passage are formed in the side wall of the mounting shaft along the circumferential direction, a limiting step for limiting the axial direction of the joint mounting seat and two ring grooves for mounting sealing rings are further formed in the side wall of the mounting shaft, and the two ring grooves are respectively located on two sides of the flow dividing holes;
the joint mounting seat and the compression nut are sequentially mounted on the mounting shaft, the joint mounting seat is axially fixed through the limiting step and the compression nut, the diversion hole is positioned in a cavity formed by the joint mounting seat and the mounting shaft, and sealing between the joint mounting seat and the mounting shaft is realized by mounting a sealing ring in the annular groove;
the number of the connectors is N, the connectors are uniformly distributed and welded on the connector mounting seat along the circumferential direction and are communicated with the inner cavity of the connector mounting seat, and then the connectors are communicated with the diversion holes after being assembled; n is more than or equal to 3;
the spray pipe assembly comprises a spray pipe, a sleeve nut, a nozzle, a fixed block and a plug; the spray pipe comprises an inlet section and a spray section which are connected in sequence, wherein the inlet section is detachably connected and communicated with the joint, and a plurality of spray holes are uniformly distributed on the side wall of the spray section; the length of the injection section is matched with the length of the low-pressure air inlet, so that the injection hole can fully cover the low-pressure air inlet; the outer sleeve nut and the nozzle are sleeved on the inlet section of the spray pipe, and the outer sleeve nut is positioned outside the nozzle; the fixed block is sleeved and welded outside the spray pipe; the outer surface of the fixed block is the fixed position of the wrench when the spray pipe is installed; the plug is inserted into and welded to the end of the jet section of the jet pipe.
2. The aircraft engine low pressure inlet in-wing cleaning tool of claim 1, wherein: and an inclined plane is processed on the outer side wall of the plug to form a milling structure, and the direction of the milling structure is consistent with the injection direction of the injection hole on the spray pipe.
3. The aircraft engine low pressure inlet in-wing cleaning tool according to claim 1 or 2, characterized in that: at least three of the diversion holes are arranged.
4. The aircraft engine low pressure inlet in-wing cleaning tool of claim 3, wherein: the connector mounting seat is integrally of a hexahedral structure, and a shaft hole penetrating from one surface to the opposite surface is formed in one surface and is used for being matched with the mounting shaft; the other four surfaces of the joint mounting seat are respectively provided with a joint mounting hole for mounting the joint, and the joint mounting holes are step holes;
the number of the connectors is four, and the connectors are respectively arranged in the connector mounting holes.
5. The aircraft engine low pressure inlet in-wing cleaning tool of claim 4, wherein: and the joint and the jet pipe form an aviation 74-degree flaring sealing structure at the joint.
6. The aircraft engine low pressure inlet in-wing cleaning tool according to claim 1 or 2, characterized in that: the cleaning agent flow passage is characterized by further comprising a dustproof cap arranged on the mounting shaft, wherein the dustproof cap is used for blocking a port of the cleaning agent flow passage in a non-use state.
7. An aeroengine low-pressure air inlet on-wing cleaning device comprises a cleaning device; the method is characterized in that: the aircraft engine low pressure inlet in-wing cleaning tool of any one of claims 1-6; the cleaning device is connected with a mounting shaft in the wing cleaning tool, and cleaning agent is fed into a cleaning agent flow passage of the mounting shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211701112.0A CN116213340A (en) | 2022-12-28 | 2022-12-28 | Tool and equipment for cleaning low-pressure air inlet on wing of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211701112.0A CN116213340A (en) | 2022-12-28 | 2022-12-28 | Tool and equipment for cleaning low-pressure air inlet on wing of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116213340A true CN116213340A (en) | 2023-06-06 |
Family
ID=86583415
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211701112.0A Pending CN116213340A (en) | 2022-12-28 | 2022-12-28 | Tool and equipment for cleaning low-pressure air inlet on wing of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116213340A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117619804A (en) * | 2024-01-25 | 2024-03-01 | 成都航利装备科技有限公司 | Turbofan engine airflow channel cleaning tool and use method |
| CN117871293A (en) * | 2024-03-11 | 2024-04-12 | 四川嘉乐地质勘察有限公司 | Self-correction-based high strain force detection method and detection device |
-
2022
- 2022-12-28 CN CN202211701112.0A patent/CN116213340A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117619804A (en) * | 2024-01-25 | 2024-03-01 | 成都航利装备科技有限公司 | Turbofan engine airflow channel cleaning tool and use method |
| CN117619804B (en) * | 2024-01-25 | 2024-05-07 | 成都航利装备科技有限公司 | Turbofan engine airflow channel cleaning tool and use method |
| CN117871293A (en) * | 2024-03-11 | 2024-04-12 | 四川嘉乐地质勘察有限公司 | Self-correction-based high strain force detection method and detection device |
| CN117871293B (en) * | 2024-03-11 | 2024-05-28 | 四川嘉乐地质勘察有限公司 | Self-correction-based high strain force detection method and detection device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN116213340A (en) | Tool and equipment for cleaning low-pressure air inlet on wing of aero-engine | |
| CN109250149B (en) | Wind tunnel test device for separation simulation of air suction type hypersonic vehicle fairing | |
| CN113680545B (en) | Noise reduction nozzle adjusted by adopting rotating structure | |
| CN115451429B (en) | Head oil supply and nozzle structure of oil slinger combustion chamber | |
| CN109911629B (en) | Novel prevent that powder from attaching wall strength powder conveying sleeve pipe | |
| CN108318252B (en) | Modular water spraying device for humidification test of inlet of gas compressor | |
| CN107671640B (en) | Grinding quick-change tool for precision part of fuel nozzle of aircraft engine and using method | |
| CN111502978A (en) | Connecting device for plunger and power end of diaphragm pump | |
| CN216207489U (en) | Auxiliary swirler fuel test tool | |
| CN214466778U (en) | Pipe joint for adjusting horizontal state of valve | |
| CN210033635U (en) | Air blow gun for cleaning automobile engine | |
| CN210548377U (en) | Multi-channel rotating device for milling head | |
| CN103267187B (en) | Fuel manifold spherical joint and tester quick connector | |
| CN221322561U (en) | Flange for air inlet pipe of automobile engine | |
| CN203363622U (en) | Grease nipple | |
| CN216617687U (en) | Gas turbine washing system ring pipe mounting structure | |
| CN104018942A (en) | Fuel manifold joint for gas turbine and gas turbine | |
| CN116213375A (en) | Aeroengine high-pressure air flow channel on-wing flushing tool and equipment | |
| CN115234912B (en) | Turbine red collar flame heating device and use method | |
| CN218935561U (en) | Pipe joint convenient to disassemble and assemble | |
| CN219967187U (en) | Clamp for adjusting coaxiality of casing | |
| CN210660394U (en) | Diesel engine high pressure fuel pipe assembly and high pressure connector fixer | |
| CN219243570U (en) | Angle gasket structure for adjusting axis direction of spray gun | |
| CN220505135U (en) | Anti-drop cutting ferrule structure and engine | |
| CN217762549U (en) | Pneumatic pipe joint |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |