An aero-engine blade surface cleaning device and method thereof

Abstract

A device and method for cleaning the surface of aero-engine blades are provided. The blade surface is cleaned by using a water immersion nozzle, a cleaning nozzle and its foamer, and a drying fan to perform water immersion, cleaning fluid cleaning, micro-explosion cleaning, dry ice cleaning, water rinsing and drying. It can efficiently and effectively remove dirt from the blade surface without scratching or damaging the blade surface.

Description

Technical Field

[0001] This application belongs to the field of aero-engine blade surface cleaning design technology, specifically relating to an aero-engine blade surface cleaning device and method. Background Technology

[0002] When an aircraft engine is operating, it ingests dust, sand, salt spray, oil, smoke, insect remains, and other debris. This debris adheres to the surfaces of the fan, booster stage, and compressor blades, causing changes in the blade shape. This leads to reduced engine efficiency, increased fuel consumption, and severely impacts engine performance, even causing serious corrosion and posing a danger. The usual method is to spray cleaning fluid into the engine through cleaning nozzles to clean the blade surfaces. However, as the engine operates for longer periods, excessive debris can accumulate on the blade surfaces, forming grime. In such cases, relying solely on cleaning fluid sprayed through nozzles is insufficient for effective cleaning. It becomes necessary to disassemble the aircraft engine, remove the blades, and perform a thorough cleaning of their surfaces.

[0003] Currently, when disassembling aircraft engines and removing blades for deep cleaning, the process is mainly done manually. This involves complex steps such as soaking, scraping, and cleaning, which is time-consuming, labor-intensive, and can easily damage the blade surface.

[0004] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0005] The purpose of this application is to provide an aero-engine blade surface cleaning device and method to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] One aspect provides an aero-engine blade surface cleaning device, comprising:

[0008] Motor-driven turntable;

[0009] The bell-shaped opening is placed horizontally with its opening facing the motor-driven turntable, and has a notch on the bottom side wall.

[0010] The nozzle is moistened with clean water and connected to the side wall above the flared mouth, with its head facing the motor-driven turntable;

[0011] The drying fan is attached to the bracket and positioned above the motor-driven turntable;

[0012] The foamer is located below the flared end, below the notch, and is filled with cleaning fluid.

[0013] The cleaning nozzle is located at the center of the flared mouth, with the head facing the inside of the flared mouth. The head end face has multiple dry ice cleaning jet holes, multiple micro-explosion cleaning jet holes surrounding the dry ice cleaning jet holes, and cleaning liquid cleaning jet holes surrounding the micro-explosion cleaning jet holes.

[0014] According to at least one embodiment of this application, the above-described aero-engine blade surface cleaning device further includes:

[0015] The bracket is attached to the side wall above the horn opening;

[0016] The nozzle is moistened with clean water, and the fan is connected to the bracket to dry it.

[0017] According to at least one embodiment of this application, in the above-mentioned aero-engine blade surface cleaning device, the cleaning nozzle has a dry ice cleaning jet chamber that is connected to each dry ice cleaning jet hole.

[0018] The aero-engine blade surface cleaning device also includes:

[0019] A dry ice pellet storage box is connected to a cleaning nozzle via a pipeline, and a dry ice cleaning jet chamber is connected to the tail of the cleaning nozzle.

[0020] The air pump, whose outlet is connected to the dry ice particle storage tank via a pipeline, can blow high-pressure air into the dry ice particle storage tank when dry ice cleaning the blade surface. This blows the dry ice particles in the storage tank into the dry ice cleaning jet chamber, where they can then be ejected through the dry ice cleaning jet orifice.

[0021] According to at least one embodiment of this application, in the above-mentioned aero-engine blade surface cleaning device, the cleaning nozzle has multiple micro-explosive cleaning jet chambers connected to each micro-explosive cleaning jet hole; and each micro-explosive cleaning jet chamber is provided with a one-way high-pressure flow limiting valve.

[0022] The aero-engine blade surface cleaning device also includes:

[0023] A clean water tank is connected to a cleaning nozzle via a pipeline. Each micro-explosive cleaning jet chamber is connected inside the cleaning nozzle. A one-way low-pressure flow limiting valve is installed on the pipeline corresponding to each micro-explosive cleaning jet chamber.

[0024] Multiple sliders are installed in each micro-explosive cleaning jet chamber; each one-way low-pressure flow limiting valve is located between the one-way high-pressure flow limiting valve and the slider.

[0025] Multiple sliders drive the connecting rod, with one end hinged to each slider at the tail of the cleaning nozzle.

[0026] Multiple sliders drive cranks, which are hinged to the other end of each slider connecting rod;

[0027] Multiple slider-driven motors are connected to individual slider-driven cranks. Upon startup, these motors, through the slider-driven cranks and connecting rods, drive the sliders to reciprocate within the micro-explosive cleaning jet chamber.

[0028] When the slider moves away from the one-way high-pressure flow limiting valve, the pressure in the cavity between the slider and the one-way high-pressure flow limiting valve decreases. After the pressure decreases to the limiting pressure of the one-way high-pressure flow limiting valve, the one-way high-pressure flow limiting valve closes. After the pressure decreases to the limiting pressure of the one-way low-pressure flow limiting valve, the one-way low-pressure flow limiting valve opens, and the clean water in the clean water tank is filled into the cavity between the slider and the one-way high-pressure flow limiting valve through the one-way low-pressure flow limiting valve.

[0029] When the slider moves toward the one-way high-pressure flow limiting valve, the pressure in the cavity between the slider and the one-way high-pressure flow limiting valve increases. After the pressure rises to the limiting pressure of the one-way low-pressure flow limiting valve, the one-way low-pressure flow limiting valve closes. After the pressure rises to the limiting pressure of the one-way high-pressure flow limiting valve, the one-way high-pressure flow limiting valve opens. The cleaning fluid in the cavity between the slider and the one-way high-pressure flow limiting valve can then be ejected through the micro-explosion cleaning jet orifice via the one-way high-pressure flow limiting valve.

[0030] According to at least one embodiment of this application, in the above-mentioned aero-engine blade surface cleaning device, each slider drive motor has a phase difference;

[0031] When the number of slider drive motors is 6, the phase difference between adjacent slider drive motors is 60°.

[0032] According to at least one embodiment of this application, in the above-mentioned aero-engine blade surface cleaning device, the cleaning nozzle has multiple cleaning liquid jet chambers connected to each cleaning liquid jet hole, and each cleaning liquid jet hole is conical.

[0033] The aero-engine blade surface cleaning device also includes:

[0034] Cleaning fluid tank;

[0035] The booster pump has its inlet connected to the cleaning fluid tank via a pipeline, and its outlet connected to the cleaning nozzle via a pipeline. The cleaning fluid jet chamber is connected to the tail of the cleaning nozzle. After starting, it can pressurize the cleaning fluid in the cleaning fluid tank and deliver it to the cleaning fluid jet chamber, whereby the cleaning fluid can then be sprayed out through the cleaning fluid jet hole.

[0036] According to at least one embodiment of this application, in the above-mentioned aero-engine blade surface cleaning device, the outer wall of the cleaning nozzle has multiple gates that connect to each cleaning fluid cleaning jet chamber.

[0037] The aero-engine blade surface cleaning device also includes:

[0038] Multiple gates are installed at various gate openings;

[0039] Multiple gate drive linkages, one end of which is hinged to each gate;

[0040] Multiple gate drive cranks are hinged to the other end of each gate drive connecting rod;

[0041] Multiple gate drive motors are connected to each gate drive crank. After starting, they can drive the gate to reciprocate into the cleaning fluid jet chamber through each gate drive crank and gate drive connecting rod, thereby changing the effective flow area of ​​the cleaning fluid jet chamber and causing the pressure and flow rate of the cleaning fluid sprayed through the cleaning fluid jet hole to change cyclically.

[0042] According to at least one embodiment of this application, in the above-mentioned aircraft engine blade surface cleaning device, the bottom edge shape of each gate is adapted to the wall surface of the cleaning fluid jet cavity, specifically, it is arc-shaped, and an arc-shaped notch is opened at the middle part of the bottom edge.

[0043] According to at least one embodiment of this application, in the above-mentioned aero-engine blade surface cleaning device, each dry ice cleaning jet hole is conical.

[0044] Each micro-blast cleaning jet hole is conical;

[0045] Each cleaning fluid jet orifice is conical.

[0046] On the other hand, a method for cleaning the surface of an aero-engine blade is provided, implemented based on the aforementioned aero-engine blade surface cleaning device, including:

[0047] Fix the blade to the motor-driven turntable, start the motor-driven turntable, and adjust it so that one side of the blade faces the horn opening.

[0048] Water is introduced into the water immersion nozzle and sprayed onto the blade surface to wet the blade surface.

[0049] Cleaning fluid is introduced into the cleaning nozzle, and the cleaning fluid is sprayed onto the blade surface through the jet orifice to clean the blade.

[0050] The cleaning fluid bubbles are sprayed into the nozzle by a foamer, and the cleaning fluid accumulates in the nozzle. Clean water is also introduced into the cleaning nozzle and sprayed onto the blade surface through a micro-explosion cleaning jet hole. The clean water sprayed from the micro-explosion cleaning jet hole punctures the cleaning fluid bubbles along the way, creating micro-explosions to clean the blades.

[0051] Dry ice particles are introduced into the cleaning nozzle and sprayed onto the blade surface through the dry ice cleaning jet orifice to perform dry ice cleaning on the blade.

[0052] Start the motor to drive the turntable, adjust it so that the other side of the blade faces the horn, and perform water immersion, cleaning solution cleaning, micro-explosion cleaning, and dry ice cleaning on the blade surface.

[0053] The motor is started to drive the turntable to rotate the blades, and clean water is introduced into the clean water immersion nozzle and sprayed onto the blade surface to rinse the blade surface with clean water.

[0054] The motor drives the turntable to rotate the blades, and the drying fan is started to dry the blade surface, thus completing the cleaning of the blade surface.

[0055] This application has at least the following beneficial technical effects:

[0056] A device and method for cleaning the surface of aero-engine blades are provided. The blade surface is cleaned by using a water immersion nozzle, a cleaning nozzle and its foamer, and a drying fan to perform water immersion, cleaning fluid cleaning, micro-explosion cleaning, dry ice cleaning, water rinsing and drying. It can efficiently and effectively remove dirt from the blade surface without scratching or damaging the blade surface. Attached Figure Description

[0057] Figure 1 This is a schematic diagram of the aero-engine blade surface cleaning device provided in the embodiments of this application;

[0058] Figure 2 This is a cross-sectional schematic diagram of the cleaning nozzle provided in an embodiment of this application;

[0059] Figure 3 This is a schematic diagram of the dry ice cleaning jet cavity, the micro-explosion cleaning jet cavity, the cleaning fluid cleaning jet cavity, and their related structures provided in the embodiments of this application;

[0060] Figure 4 This is a schematic diagram of the gate, gate drive linkage, gate drive crank, gate drive motor and cleaning fluid cleaning jet cavity provided in the embodiments of this application;

[0061] in:

[0062] 1-Motor-driven turntable; 2-Flute mouth; 3-Clean water immersion nozzle; 4-Drying fan; 5-Foamer; 6-Cleaning nozzle; 7-Support; 8-Dry ice pellet storage tank; 9-Air pump; 10-One-way high-pressure flow limiting valve; 11-Clean water tank; 12-One-way low-pressure flow limiting valve; 13-Slider; 14-Slider drive linkage; 15-Slider drive crank; 16-Slider drive motor; 17-Cleaning fluid tank; 18-Booster pump; 19-Gate; 20-Gate drive linkage; 21-Gate drive crank; 22-Gate drive motor;

[0063] A-Dry ice cleaning of the jet cavity;

[0064] B-Micro-explosive cleaning jet chamber;

[0065] C-cleaning solution cleans the jet cavity.

[0066] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0067] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0068] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms indicating direction used in this application description are used only to indicate relative direction or positional relationship; when the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "comprising" as used in this application description indicates that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, but does not exclude other elements or objects.

[0069] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0070] A device for cleaning the surface of aero-engine blades is provided, such as... Figure 1 As shown, it includes:

[0071] Motor-driven turntable 1;

[0072] The flared mouth 2 is placed horizontally with its opening facing the motor-driven turntable 1, and has a notch on its bottom side wall;

[0073] The nozzle 3 is moistened with clean water and connected to the side wall above the horn 2, with its head facing the motor-driven turntable 1;

[0074] The drying fan 4 is connected to the bracket 3 and is positioned above the motor-driven turntable 1;

[0075] Foamer 5 is located below the horn 2, below the notch, and is filled with cleaning liquid, which may be soapy water.

[0076] The cleaning nozzle 6 is located at the center of the flared nozzle 2, with its head facing inwards towards the flared nozzle 2. The head end face has multiple dry ice cleaning jet holes, multiple micro-explosion cleaning jet holes surrounding the dry ice cleaning jet holes, and cleaning fluid cleaning jet holes surrounding the micro-explosion cleaning jet holes. Figure 2 As shown.

[0077] The air-engine blade surface cleaning device disclosed in the above embodiments is used to clean the blade surface. The specific steps are as follows:

[0078] a. Fix the blade to the motor-driven turntable 1. Specifically, a tenon groove can be opened on the surface of the motor-driven turntable 1. The tenon at the root of the blade is inserted into the tenon groove. Start the motor-driven turntable 1 and adjust it so that one side of the blade faces the horn mouth 2.

[0079] b. Pass clean water into the clean water wetting nozzle 3 and spray it onto the blade surface to wet the blade surface with clean water. The wetting time can be 1 minute. During this process, the clean water sprayed onto the blade surface by the clean water wetting nozzle 3 can be controlled to be low pressure and low speed. Then let it stand for 1 minute.

[0080] c. Introduce cleaning fluid into the cleaning nozzle 6 and spray the cleaning fluid through the cleaning jet orifice onto the blade surface to clean the blade. The cleaning time can be 2-3 minutes. During this process, the pressure and speed of the cleaning fluid sprayed onto the blade surface through the cleaning jet orifice can be controlled to remove dirt with weak adhesion from the blade surface.

[0081] d. The foamer 5 sprays cleaning fluid bubbles into the nozzle 2, where the cleaning fluid accumulates. Clean water is also introduced into the cleaning nozzle 6 and sprayed onto the blade surface through the micro-explosion cleaning jet orifice. The clean water sprayed from the micro-explosion cleaning jet orifice punctures the cleaning fluid bubbles along the way, creating micro-explosions to clean the blades. The micro-explosion cleaning can last for 2-3 minutes. During this process, the high pressure and high speed of the clean water sprayed onto the blade surface through the micro-explosion cleaning jet orifice can be controlled. The generated micro-explosion jet can remove dirt with strong adhesion from the blade surface.

[0082] e. Introduce dry ice particles into the cleaning nozzle 6 and spray them onto the blade surface through the dry ice cleaning jet hole to perform dry ice cleaning on the blade. The dry cleaning time can be 2-3 minutes. During this process, the dry ice particles will impact the blade surface at high speed, break, and generate explosive force, which can remove the dirt with extremely strong adhesion on the blade surface. At the same time, it will vaporize instantly and will not cause secondary pollution to the blade surface.

[0083] f. Start the motor to drive the turntable 1, adjust it so that the other side of the blade faces the horn mouth 2, and repeat the above steps a to e to perform water immersion, cleaning solution cleaning, micro-explosion cleaning, and dry ice cleaning on the blade surface.

[0084] g. Start the motor to drive the turntable 1 to rotate the blades, and introduce clean water into the clean water wetting nozzle 3 to spray onto the blade surface to rinse the blade surface with clean water. The rinsing time can be 1 minute. During this process, the clean water sprayed onto the blade surface by the clean water wetting nozzle 3 can be controlled to be low pressure and low speed to wash away the dirt remaining on the blade surface. Afterwards, a protective agent can be sprayed onto the blade surface.

[0085] h. Start the motor to drive the turntable 1 to rotate the blades, start the drying fan 4 to dry the blade surface, and complete the cleaning of the blade surface.

[0086] The aircraft engine blade surface cleaning device disclosed in the above embodiments can clean the blade surface by using a water immersion nozzle 3, a cleaning nozzle 6 and its foamer 5, and a drying fan 4 to perform water immersion, cleaning fluid cleaning, micro-explosion cleaning, dry ice cleaning, water rinsing and drying. It can efficiently and effectively remove dirt from the blade surface without scratching or damaging the blade surface.

[0087] In some optional embodiments, the above-described aero-engine blade surface cleaning device further includes:

[0088] The bracket 7 is connected to the upper side wall of the horn mouth 2;

[0089] The nozzle 3 is moistened with clean water, and the fan 4 is connected to the bracket 7.

[0090] In some alternative embodiments, in the above-mentioned aero-engine blade surface cleaning device, the cleaning nozzle 6 has a dry ice cleaning jet cavity A, which is connected to each dry ice cleaning jet hole, and each dry ice cleaning jet hole is conical.

[0091] The aero-engine blade surface cleaning device also includes:

[0092] The dry ice pellet storage box 8 is connected to the cleaning nozzle 6 via a pipeline, and the dry ice cleaning jet chamber A is connected to the tail of the cleaning nozzle 6.

[0093] Air pump 9, whose outlet is connected to dry ice particle storage tank 8 via a pipeline, is activated when dry ice cleaning is performed on the blade surface. It blows high-pressure air into the dry ice particle storage tank 8, propelling the dry ice particles from the tank into the dry ice cleaning jet chamber A. The dry ice particles are then sprayed onto the blade surface through the dry ice cleaning jet orifice. Figure 3 As shown.

[0094] In some optional embodiments, in the above-mentioned aero-engine blade surface cleaning device, the cleaning nozzle 6 has multiple micro-explosive cleaning jet chambers B, which are connected to each micro-explosive cleaning jet hole, and each micro-explosive cleaning jet hole is conical; a one-way high-pressure flow limiting valve 10 is provided in each micro-explosive cleaning jet chamber B.

[0095] The aero-engine blade surface cleaning device also includes:

[0096] The clean water tank 11 is connected to the cleaning nozzle 6 through a pipeline. Each micro-explosive cleaning jet chamber B is connected inside the cleaning nozzle 6. A one-way low-pressure flow limiting valve 12 is installed on the pipeline corresponding to each micro-explosive cleaning jet chamber B.

[0097] Multiple sliders 13 are set in each micro-blasting cleaning jet chamber B; each one-way low-pressure flow limiting valve 12 is located between the one-way high-pressure flow limiting valve 10 and the slider 13.

[0098] Multiple slider drive linkages 14 are hinged at one end to each slider 13 at the tail of the cleaning nozzle 6.

[0099] Multiple sliders drive cranks 15, which are hinged to the other end of each slider connecting rod 14;

[0100] Multiple slider drive motors 16 are connected to slider drive cranks 15. These motors are activated during micro-explosive cleaning of the blade surface. Through the slider drive cranks 15 and slider drive connecting rods 14, the sliders 13 reciprocate within the micro-explosive cleaning jet chamber B. When the slider 13 moves away from the one-way high-pressure limiting valve 10, the pressure in the cavity between the slider 13 and the one-way high-pressure limiting valve 10 decreases. Once the pressure drops to the limiting pressure of the one-way high-pressure limiting valve 10, the one-way high-pressure limiting valve 10 closes. Once the pressure drops to the limiting pressure of the one-way low-pressure limiting valve 12, the one-way low-pressure limiting valve 12 opens, and the clean water tank 1... The clean water in section 1 is injected into the cavity between slider 13 and one-way high-pressure flow limiting valve 10 through one-way low-pressure flow limiting valve 12. When slider 13 moves toward one-way high-pressure flow limiting valve 10, the pressure in the cavity between slider 13 and one-way high-pressure flow limiting valve 10 increases. After the pressure rises to the limiting pressure of one-way low-pressure flow limiting valve 12, one-way low-pressure flow limiting valve 12 closes. After the pressure rises to the limiting pressure of one-way high-pressure flow limiting valve 10, one-way high-pressure flow limiting valve 10 opens. The cleaning fluid in the cavity between slider 13 and one-way high-pressure flow limiting valve 10 can be sprayed onto the blade surface through the micro-explosion cleaning jet orifice of one-way high-pressure flow limiting valve 10. Figure 3 As shown.

[0101] In some alternative embodiments, to improve the cleaning effect on the blade surface, the above-mentioned aero-engine blade surface cleaning device is designed to have a phase difference between each slider drive motor 16 when performing micro-explosive cleaning on the blade surface, so that each micro-explosive cleaning jet hole can sequentially and intermittently spray clean water onto the blade surface. For example, when there are 6 slider drive motors 16, the phase difference between adjacent slider drive motors 16 can be designed to be 60°.

[0102] In some optional embodiments, in the above-mentioned aero-engine blade surface cleaning device, the cleaning nozzle 6 has multiple cleaning fluid jet chambers C, which are connected to each cleaning fluid jet hole, and each cleaning fluid jet hole is conical.

[0103] The aero-engine blade surface cleaning device also includes:

[0104] Cleaning fluid tank 17;

[0105] A booster pump 18 has its inlet connected to a cleaning fluid tank 17 via a pipeline, and its outlet connected to a cleaning nozzle 6 via a pipeline. The cleaning nozzle 6 is connected to a cleaning fluid jet chamber C at its tail. When cleaning the blade surface with the cleaning fluid, the pump is activated, pressurizing the cleaning fluid in the tank 17 and delivering it to the cleaning fluid jet chamber C. The cleaning fluid can then be sprayed onto the blade surface through the jet orifice. Figure 3 As shown.

[0106] In some alternative embodiments, in the above-described aero-engine blade surface cleaning device, the outer wall of the cleaning nozzle 6 has multiple gates that connect to each cleaning fluid cleaning jet cavity C.

[0107] The aero-engine blade surface cleaning device also includes:

[0108] Multiple gates 19 are installed in each gate opening;

[0109] Multiple gate drive linkages 20 are hinged at one end to each gate 19;

[0110] Multiple gate drive cranks 21 are hinged to the other end of each gate drive link 20;

[0111] Multiple gate drive motors 22, connected to gate drive cranks 21, are activated when the blade surface is cleaned with cleaning fluid. These motors, via the gate drive cranks 21 and gate drive connecting rods 20, drive the gates 19 to reciprocate within the cleaning fluid jet chamber C. This alters the effective flow area of ​​the cleaning fluid jet chamber C, causing a cyclical change in the pressure and flow rate of the cleaning fluid sprayed onto the blade surface through the jet orifices, thereby improving the cleaning effect on the blade surface. Figure 3 As shown.

[0112] In some optional embodiments, in the above-mentioned aircraft engine blade surface cleaning device, the bottom edge shape of each gate 19 is adapted to the wall surface of the cleaning fluid jet cavity C, specifically it can be designed as an arc shape, and an arc-shaped notch is opened at the middle part of the bottom edge, such as... Figure 4 As shown.

[0113] On the other hand, a method for cleaning the surface of an aero-engine blade is provided, implemented based on the aforementioned aero-engine blade surface cleaning device, including:

[0114] a. Fix the blade to the motor-driven turntable 1, start the motor-driven turntable 1, and adjust it so that one side of the blade faces the horn mouth 2.

[0115] b. Pass clean water into the clean water immersion nozzle 3 and spray it onto the blade surface to immerse the blade surface with clean water;

[0116] c. Introduce cleaning fluid into cleaning nozzle 6, and spray the cleaning fluid through the jet orifice onto the blade surface to clean the blade.

[0117] d. The foamer 5 sprays cleaning fluid bubbles into the horn 2, the cleaning fluid accumulates in the horn 2, and clean water is introduced into the cleaning nozzle 6. The micro-explosion cleaning jet is sprayed onto the blade surface. The clean water sprayed from the micro-explosion cleaning jet punctures the cleaning fluid bubbles along the way, producing micro-explosions, and performing micro-explosion cleaning on the blade.

[0118] e. Introduce dry ice particles into the cleaning nozzle 6 and spray them onto the blade surface through the dry ice cleaning jet hole to perform dry ice cleaning on the blade.

[0119] f. Start the motor to drive the turntable 1, adjust it so that the other side of the blade faces the horn mouth 2, and repeat the above steps a to e to perform water immersion, cleaning solution cleaning, micro-explosion cleaning, and dry ice cleaning on the blade surface.

[0120] g. Start the motor to drive the turntable 1 to rotate the blades, and introduce clean water into the clean water immersion nozzle 3 to spray onto the blade surface and rinse the blade surface with clean water.

[0121] h. Start the motor to drive the turntable 1 to rotate the blades, start the drying fan 4 to dry the blade surface, and complete the cleaning of the blade surface.

[0122] The method for cleaning the surface of aero-engine blades disclosed in the above embodiments is implemented based on the aero-engine blade surface cleaning device disclosed in the above embodiments. The description is relatively simple. For specific details, please refer to the relevant description of the aero-engine blade surface cleaning device. The technical effects can also be referred to the technical effects of the relevant parts of the aero-engine blade surface cleaning device. It will not be repeated here.

[0123] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. Similar or identical parts between embodiments can be referred to mutually. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined to obtain new embodiments.

[0124] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A device for cleaning the surface of aero-engine blades, characterized in that, include: Motor-driven turntable (1); The flared mouth (2) is placed horizontally with the opening facing the motor-driven turntable (1), and has a notch on the bottom side wall; The water-soaked nozzle (3) is connected to the upper side wall of the horn mouth (2), with its head facing the motor-driven turntable (1). The drying fan (4) is connected to the bracket (3) and is located above the motor-driven turntable (1); The foamer (5) is located below the horn (2), below the notch, and is filled with cleaning fluid. The cleaning nozzle (6) is located at the center of the horn mouth (2), with the head facing the inside of the horn mouth (2). The head end face has multiple dry ice cleaning jet holes, multiple micro-explosion cleaning jet holes surrounding the dry ice cleaning jet holes, and cleaning liquid cleaning jet holes surrounding the micro-explosion cleaning jet holes. The cleaning nozzle (6) has a dry ice cleaning jet chamber (A) that connects to each dry ice cleaning jet hole; The aero-engine blade surface cleaning device also includes: A dry ice pellet storage box (8) is connected to a cleaning nozzle (6) via a pipeline, and a dry ice cleaning jet chamber (A) is connected to the tail of the cleaning nozzle (6). The air pump (9) is connected to the dry ice particle storage box (8) through a pipeline. When dry ice cleaning is performed on the blade surface, it can blow high-pressure air into the dry ice particle storage box (8) after starting, and blow the dry ice particles in the dry ice particle storage box (8) into the dry ice cleaning jet chamber (A), and the dry ice particles can then be sprayed out through the dry ice cleaning jet hole. The cleaning nozzle (6) has multiple micro-explosive cleaning jet chambers (B) that are connected to each micro-explosive cleaning jet hole; each micro-explosive cleaning jet chamber (B) is equipped with a one-way high-pressure flow limiting valve (10). The aero-engine blade surface cleaning device also includes: A clean water tank (11) is connected to a cleaning nozzle (6) via a pipeline. Each micro-explosion cleaning jet chamber (B) is connected inside the cleaning nozzle (6). A one-way low-pressure flow limiting valve (12) is installed on the pipeline corresponding to each micro-explosion cleaning jet chamber (B). Multiple sliders (13) are set in each micro-explosive cleaning jet chamber (B); each one-way low-pressure flow limiting valve (12) is located between the one-way high-pressure flow limiting valve (10) and the slider (13); Multiple slider drive linkages (14) are hinged at one end to each slider (13) at the tail of the cleaning nozzle (6); Multiple sliders drive cranks (15), which are hinged to the other end of each slider connecting rod (14); Multiple slider drive motors (16) are connected to various slider drive cranks (15). After startup, they can drive the slider (13) to reciprocate within the micro-explosive cleaning jet chamber (B) via the various slider drive cranks (15) and slider drive connecting rods (14). When the slider (13) moves away from the one-way high pressure limiting valve (10), the pressure in the cavity between the slider (13) and the one-way high pressure limiting valve (10) decreases. After the pressure decreases to the limiting pressure of the one-way high pressure limiting valve (10), the one-way high pressure limiting valve (10) closes. After the pressure decreases to the limiting pressure of the one-way low pressure limiting valve (12), the one-way low pressure limiting valve (12) opens. The clean water in the clean water tank (11) is filled into the cavity between the slider (13) and the one-way high pressure limiting valve (10) through the one-way low pressure limiting valve (12). When the slider (13) moves toward the one-way high pressure limiting valve (10), the pressure in the cavity between the slider (13) and the one-way high pressure limiting valve (10) increases. After the pressure increases to the limiting pressure of the one-way low pressure limiting valve (12), the one-way low pressure limiting valve (12) closes. After the pressure increases to the limiting pressure of the one-way high pressure limiting valve (10), the one-way high pressure limiting valve (10) opens. The cleaning fluid in the cavity between the slider (13) and the one-way high pressure limiting valve (10) can be sprayed out through the micro-explosion cleaning jet hole via the one-way high pressure limiting valve (10).

2. The aero-engine blade surface cleaning device according to claim 1, characterized in that, Also includes: The bracket (7) is connected to the side wall above the horn opening (2); The nozzle (3) is moistened with water and the drying fan (4) is connected to the bracket (7).

3. The aero-engine blade surface cleaning device according to claim 2, characterized in that, Each slider drive motor (16) has a phase difference; When the number of slider drive motors (16) is 6, the phase difference between adjacent slider drive motors (16) is 60°.

4. The aero-engine blade surface cleaning device according to claim 3, characterized in that, The cleaning nozzle (6) has multiple cleaning fluid jet chambers (C) that are connected to each cleaning fluid jet hole, and each cleaning fluid jet hole is conical. The aero-engine blade surface cleaning device also includes: Cleaning fluid tank (17); The booster pump (18) has its inlet connected to the cleaning fluid tank (17) via a pipeline, and its outlet connected to the cleaning nozzle (6) via a pipeline. The cleaning fluid cleaning jet chamber (C) is connected to the tail of the cleaning nozzle (6). After starting, it can pressurize the cleaning fluid in the cleaning fluid tank (17) and deliver it to the cleaning fluid cleaning jet chamber (C), so that the cleaning fluid can be sprayed out through the cleaning fluid jet hole.

5. The aero-engine blade surface cleaning device according to claim 4, characterized in that, The outer wall of the cleaning nozzle (6) has multiple gates that connect to each cleaning fluid cleaning jet chamber (C). The aero-engine blade surface cleaning device also includes: Multiple gates (19) are installed in each gate opening; Multiple gate drive linkages (20) are hinged at one end to each gate (19); Multiple gate drive cranks (21) are hinged to the other end of each gate drive link (20); Multiple gate drive motors (22) are connected to each gate drive crank (21). After starting, they can drive the gate (19) to reciprocate into the cleaning fluid jet chamber (C) through each gate drive crank (21) and gate drive connecting rod (20), so as to change the effective flow area of ​​the cleaning fluid jet chamber (C) and make the pressure and flow rate of the cleaning fluid sprayed through the cleaning fluid jet hole change cyclically.

6. The aero-engine blade surface cleaning device according to claim 5, characterized in that, The bottom edge shape of each gate (19) is adapted to the wall of the cleaning fluid jet cavity (C), specifically an arc shape, and an arc-shaped notch is opened in the middle part of the bottom edge.

7. The aero-engine blade surface cleaning device according to claim 6, characterized in that, Each dry ice cleaning jet orifice is conical; Each micro-blast cleaning jet hole is conical; Each cleaning fluid jet orifice is conical.

8. A method for cleaning the surface of an aero-engine blade, characterized in that, The implementation of the aero-engine blade surface cleaning device according to claim 7 includes: Fix the blade to the motor-driven turntable (1), start the motor-driven turntable (1), and adjust it so that one side of the blade faces the horn opening (2). Water is introduced into the water immersion nozzle (3) and sprayed onto the blade surface to immerse the blade surface in water. Cleaning fluid is introduced into the cleaning nozzle (6) and sprayed onto the blade surface through the cleaning nozzle to clean the blade. The cleaning fluid bubbles are sprayed into the horn (2) by the foamer (5), the cleaning fluid accumulates in the horn (2), and clean water is introduced into the cleaning nozzle (6). The micro-explosion cleaning jet is sprayed onto the blade surface. The clean water sprayed from the micro-explosion cleaning jet punctures the cleaning fluid bubbles along the way, generating micro-explosions, and micro-explosion cleaning is performed on the blade. Dry ice particles are introduced into the cleaning nozzle (6) and sprayed onto the blade surface through the dry ice cleaning jet hole to clean the blade with dry ice. Start the motor to drive the turntable (1), adjust it so that the other side of the blade faces the horn mouth (2), and perform water immersion, cleaning solution cleaning, micro-explosion cleaning, and dry ice cleaning on the blade surface; Start the motor to drive the turntable (1) to rotate the blades, and pass clean water into the clean water immersion nozzle (3) to spray onto the blade surface and rinse the blade surface with clean water. Start the motor to drive the turntable (1) to rotate the blades, start the drying fan (4) to dry the blade surface and complete the cleaning of the blade surface.

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