Ultrasonic cleaning device and method for inner cavity of aero-engine blade

Abstract

The invention belongs to the field of ultrasonic cleaning, and relates to an ultrasonic cleaning device and method for an inner cavity of an aero-engine blade. Ultrasonic vibration can be generated on the blade, cavitation and grinding materials of the inner cavity of the blade are excited, and high-efficiency and high-quality cleaning of sediments in the inner cavity of the blade is achieved. According to the technical scheme, the device comprises an ultrasonic generator, a fixed end, an ultrasonic excitation mechanism, a first tool head and a second tool head. The fixed end is fixed relative to the ground. An ultrasonic excitation mechanism is arranged at the opposite position of the fixed end and connected with an ultrasonic generator. The first tool head comprises a first attaching face, the first attaching face is attached to the surface of the corresponding position of the to-be-cleaned workpiece, and the first tool head is fixed to the fixed end or the ultrasonic excitation mechanism. The first tool head comprises a first binding face, the second tool head comprises a second binding face, the second binding face is attached to the surface of the corresponding position of the to-be-cleaned workpiece, the to-be-cleaned workpiece is clamped between the first tool head and the second tool head, and the second tool head is fixed to the fixed end or the ultrasonic excitation mechanism.

Description

Technical Field

[0001] The invention belongs to the field of ultrasonic cleaning, and relates to an ultrasonic cleaning device and method for the inner cavity of an aircraft engine blade. Background Art

[0002] Aircraft engine blades operate in harsh working environments for a long time, facing the challenges of high temperature, high pressure and high strain load. Aviation fuel and its combustion products will deposit in the inner cavity of the blade to form a hard and brittle carbon scale layer. These carbon scale layers will block the internal cooling channels of the blades, seriously reducing the cooling efficiency and service life of the blades, posing a potential threat to the safety performance of the aircraft engine, so they must be thoroughly removed.

[0003] At present, the methods for cleaning the inner cavity deposits of blades mainly include manual cleaning, solvent immersion and ultrasonic cleaning. However, manual cleaning is inefficient and costly, and solvent immersion is almost ineffective for thicker deposits. In the ultrasonic cleaning method, the traditional ultrasonic cavitation effect has limited cleaning effect due to the complex flow path in the blade cavity. Other methods, such as liquid-free focused ultrasonic cleaning (CN103128081A), apply focused ultrasonic waves to the blade tenon position to remove the inner cavity deposits by inducing the blade tenon to vibrate. However, the energy loss of ultrasonic waves during the propagation from the blade tenon to the blade body is large, and the inner cavity deposits far away from the blade tenon are not completely removed. In addition, there is an embedded contact microporous ultrasonic cleaning method, which clamps the two ends of the blade and uses ultrasonic excitation of metal sand to achieve the purpose of removing the inner cavity deposits. However, this method is not effective in removing deposits in specific areas.

[0004] Based on the above problems, the present invention proposes an ultrasonically excited wet abrasive cleaning device for deposits in the inner cavity of aircraft engine blades, which can generate strong ultrasonic vibrations at any local position of the blade and thereby stimulate cavitation and abrasives in the inner cavity of the blade, thereby achieving efficient and high-quality cleaning of deposits in the inner cavity of the blade. Summary of the invention

[0005] In order to overcome the defects in the above-mentioned related technologies, on the one hand, the present invention proposes an ultrasonic cleaning device for the inner cavity of an aircraft engine blade, which can generate strong ultrasonic vibrations at any local position of the blade and thereby stimulate cavitation and abrasives in the inner cavity of the blade, thereby achieving efficient and high-quality cleaning of deposits in the inner cavity of the blade.

[0006] In order to achieve the above technical objectives, the present invention provides an ultrasonic cleaning device for the inner cavity of an aircraft engine blade. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade comprises: an ultrasonic generator, a fixed end, an ultrasonic excitation mechanism, a first tool head and a second tool head. At least one fixed end is fixed relative to the ground. An ultrasonic excitation mechanism is arranged at a relative position of each fixed end, and the ultrasonic excitation mechanism is connected to the ultrasonic generator. The first tool head comprises a first fitting surface, and the first fitting surface of at least one first tool head fits the surface at the corresponding position of the workpiece to be cleaned, and each first tool head is fixed to a fixed end or an ultrasonic excitation mechanism. The second tool head comprises a second fitting surface, and the second fitting surface of at least one second tool head fits the surface at the corresponding position of the workpiece to be cleaned, and the at least one first tool head and the at least one second tool head clamp the workpiece to be cleaned to the middle, and each second tool head is fixed to a fixed end or an ultrasonic excitation mechanism.

[0007] Preferably, a first connection hole is provided on the side of the first tool head away from the first fitting surface. A second connection hole is provided on the side of the second tool head away from the second fitting surface. The fixed end includes a fixed connector, one end of which is adapted to the first connection hole and the second connection hole, and the fixed end is fixedly connected to the first tool head or the second tool head through the fixed connector.

[0008] Preferably, the ultrasonic excitation mechanism comprises: a piezoelectric transducer, a horn and a rectangular tool head. The piezoelectric transducer is connected to the ultrasonic generator, and the piezoelectric transducer is fixed relative to the ground. The output end of the piezoelectric transducer is fixedly connected to the horn. The rectangular tool head is a cube, the output end of the horn is fixedly connected to the rectangular tool head, and the first tool head or the second tool head is fixed to the side of the rectangular tool head away from the horn.

[0009] Preferably, the aircraft engine blade inner cavity ultrasonic cleaning device also includes a bracket. The bracket includes: a fixed platform, a fixed frame and a movable frame. The fixed platform is fixed to the ground, and the fixed platform includes a through slot, one side of the through slot is provided with the at least one first tool head, and the other side of the through slot is provided with the at least one second tool head. The fixed frame is fixed to the other side of the through slot. The movable frame is fixed to one side of the through slot, and at least one fixed connecting member is provided on the movable frame, and the fixed connecting member is configured to fasten the movable frame to the fixed frame, and at least one ultrasonic excitation mechanism is fixed on the movable frame.

[0010] Preferably, the movable frame comprises: a ball screw and a pressure sensor. At least one ball screw is fixed to a fixed platform on one side of the through slot, and a nut of each ball screw is fixedly connected to a corresponding fixed end. A pressure sensor is arranged between each fixed end and the corresponding first tool head or second tool head.

[0011] Preferably, the fixed frame further includes: a vertical truss, a support truss and an adjustment truss. The vertical truss is fixed to the ground. The support truss is fixed to the vertical truss, and the support truss includes at least two support rods arranged in parallel, the support rods are straight rods, and grooves are provided on the two support rods, and the plane where the center lines of the two support rods are located is perpendicular to the extension direction of the threaded rod of the ball screw. The adjustment truss is arranged on the support truss, and the adjustment truss has a tendency to reciprocate along the support rod, and the adjustment truss includes at least two adjustment rods arranged in parallel, the adjustment rods are straight rods, and grooves are provided on the two adjustment rods, and the plane where the center lines of the two adjustment rods are located is perpendicular to the extension direction of the threaded rod of the ball screw, and the adjustment rod is perpendicular to the support rod, and at least one ultrasonic excitation mechanism is arranged between the adjustment rods.

[0012] Preferably, the fixing frame further comprises restraining columns. The restraining columns are straight rods, at least four of which are fixed on a fixing table around the through slot, and the restraining columns are configured to prevent the object to be cleaned from moving to a range outside the through slot.

[0013] On the other hand, the present invention also provides an ultrasonic cleaning method for the inner cavity of an aircraft engine blade, which is applicable to the ultrasonic cleaning device for the inner cavity of an aircraft engine blade in the above-mentioned aspect. The ultrasonic cleaning method for the inner cavity of an aircraft engine blade comprises: filling wet abrasive particles into the inner cavity of the aircraft engine blade, and sealing the inner cavity opening of the aircraft engine blade. A first tool head is fitted to the outer side wall of the aircraft engine blade, and a second tool head is fitted to the other outer side wall of the aircraft engine blade, so that the first tool head and the second tool head clamp the aircraft engine blade. One of the first tool head and the second tool head is controlled to generate ultrasonic vibration, and the ultrasonic vibration is transmitted to the outer side wall of the aircraft engine blade.

[0014] Preferably, the method of filling wet abrasive particles into the inner cavity of the aircraft engine blade further comprises: mixing abrasive particles and liquid and stirring them evenly and filling them into the inner cavity of the aircraft engine blade. The volume of the abrasive particles accounts for 30% to 70% of the inner cavity space of the aircraft engine blade. The volume of the liquid accounts for 10% to 30% of the inner cavity space of the aircraft engine blade. The abrasive particles are 0.5 to 2 mm silicon carbide or steel balls, and the liquid is a weak acid solution or water.

[0015] Preferably, the method of transmitting ultrasonic vibration to the outer side wall of the aircraft engine blade includes: controlling the ultrasonic frequency of the first tool head or the second tool head so that the corresponding side of the aircraft engine blade enters the optimal resonance state. The one of the first tool head and the second tool head that does not generate ultrasonic vibration is brought closer to the aircraft engine blade so that the gap between the one of the first tool head and the second tool head that generates ultrasonic vibration and the aircraft engine blade is reduced until the ultrasonic vibration is introduced into the inner cavity of the aircraft engine blade at the microscopic level. The optimal resonance state means that the ultrasonic vibration mode of the first tool head or the second tool head is longitudinal ultrasonic vibration, and the vibration amplitude is the largest.

[0016] The beneficial effects of the present invention are: The present invention adopts a first tool head and a second tool head, which are arranged in close contact with the aircraft engine blade, to transmit ultrasonic vibration to the inside of the aircraft engine blade, thereby completing the cleaning work of the inside of the aircraft engine blade with abrasive particles, so that the cleaning operation of the inner cavity of the aircraft engine blade can be completed more efficiently and with high quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the drawings required for use in the embodiments or related technical descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 A structural diagram of the present invention; Figure 2 Another structural diagram of the present invention; Figure 3 is a structural diagram of a first tool head of the present invention; Figure 4 is a structural diagram of a second tool head of the present invention; Figure 5 It is a structural diagram of the ultrasonic excitation mechanism and the first tool head of the present invention; Figure 6 It is a structural diagram of the ultrasonic excitation mechanism and the second tool head of the present invention; Figure 7 It is another structural diagram of the present invention; Figure 8 It is a structural diagram of the fixing platform and the fixing frame of the present invention; Fig. 9 A working state diagram of a plurality of first tool heads and a plurality of second tool heads of the present invention; Fig.10This is another working state diagram of the multiple first tool heads and the multiple second tool heads of the present invention. DETAILED DESCRIPTION

[0019] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0020] In the description of the present invention, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0021] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0022] like Figures 1 to 10 As shown, some embodiments of the present invention provide an ultrasonic cleaning device for the inner cavity of an aircraft engine blade. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade comprises: an ultrasonic generator 1, a fixed end 2, an ultrasonic excitation mechanism 3, a first tool head 4 and a second tool head 5. At least one fixed end 2 is fixed relative to the ground. An ultrasonic excitation mechanism 3 is arranged at a relative position of each fixed end 2, and the ultrasonic excitation mechanism 3 is connected to the ultrasonic generator 1. The first tool head 4 comprises a first fitting surface 41, and the first fitting surface 41 of at least one first tool head 4 fits the surface at the corresponding position of the workpiece 6 to be cleaned, and each first tool head 4 is fixed to a fixed end 2 or an ultrasonic excitation mechanism 3. The second tool head 5 comprises a second fitting surface 51, and the second fitting surface 51 of at least one second tool head 5 fits the surface at the corresponding position of the workpiece 6 to be cleaned, and the at least one first tool head 4 and the at least one second tool head 5 clamp the workpiece 6 to be cleaned to the middle, and each second tool head 5 is fixed to a fixed end 2 or an ultrasonic excitation mechanism 3.

[0023] In some examples, the fixed end 2 and the ultrasonic excitation mechanism 3 are arranged opposite to each other, and a plurality of first tool heads 4 and a plurality of second tool heads 5 are arranged between the fixed end 2 and the ultrasonic excitation mechanism 3. When the first tool head 4 is fixed to the end of the fixed end 2 facing the ultrasonic excitation mechanism 3, the second tool head 5 is fixed to the end of the ultrasonic excitation mechanism 3 facing the fixed end 2, and the ultrasonic excitation mechanism 3 is connected to the ultrasonic generator 1, so that the ultrasonic vibration is transmitted from the ultrasonic generator to the second tool head 5 through the ultrasonic excitation mechanism 3 in sequence.

[0024] The parts to be cleaned, such as aircraft engine blades, are clamped between the first tool head 4 and the second tool head 5. The aircraft engine blades may be hollow blades. When the aircraft engine burns inside, a carbon scale layer is deposited in the inner cavity of the blades. Abrasives and cleaning fluids may be poured into the inner cavity of the aircraft engine blades, and the open end of the inner cavity of the aircraft engine blades may be closed. Multiple second tool heads 5 may be attached to the outer surface of the aircraft engine blades, and ultrasonic vibrations may be transmitted to the aircraft engine blades, thereby causing the cleaning fluid and abrasives in the inner cavity of the aircraft engine blades to vibrate ultrasonically, and the carbon scale layer deposited in the inner cavity of the aircraft engine blades may be cleaned in turn.

[0025] The present application can transmit ultrasonic vibrations to the inner cavity through the outer surface of the aircraft engine blade, so as to fully clean the inner cavity of the aircraft engine blade. At the same time, the cleaning efficiency is higher than that of manual cleaning and solvent immersion.

[0026] In some embodiments, a first connection hole is provided on the side of the first tool head 4 away from the first fitting surface 41. A second connection hole is provided on the side of the second tool head 5 away from the second fitting surface 51. The fixed end 2 includes a fixed connector, one end of which is adapted to the first connection hole and the second connection hole, and the fixed end 2 is fixedly connected to the first tool head 4 or the second tool head 5 through the fixed connector.

[0027] In some examples, the first tool head 4 may be a block-shaped structure, and a first fitting surface 41 is provided on the first tool head 4. The first fitting surface 41 may be adapted to the outer protruding curved surface of the aircraft engine blade, that is, the first fitting surface 41 may be closely fitted to the outer protruding curved surface of the aircraft engine blade. Similarly, the second tool head 5 may be a block-shaped structure, and a second fitting surface 51 is provided on the second tool head 5. The second fitting surface 51 may be adapted to the outer protruding curved surface of the aircraft engine blade, that is, the second fitting surface 51 may be closely fitted to the outer protruding curved surface of the aircraft engine blade.

[0028] A plurality of second tool heads 5 can be attached to the aircraft engine blade, and the inner cavity corresponding to the aircraft engine blade to which the plurality of second tool heads 5 are attached has a carbon scale layer. A plurality of first tool heads 4 are attached to the aircraft engine blade, and are arranged opposite to the plurality of second tool heads 5. The ultrasonic generator 1 is started to ultrasonically vibrate the plurality of second tool heads 5, and the plurality of second tool heads 5 transmit the ultrasonic vibration through the aircraft engine blade into its inner cavity, so that the cleaning liquid and the abrasive generate ultrasonic vibration, and the carbon scale layer at the position is cleaned. Similarly, the carbon scale layer at other positions in the inner cavity of the aircraft engine blade can be cleaned in the above manner.

[0029] In some embodiments, the ultrasonic excitation mechanism 3 includes: a piezoelectric transducer 31, a horn 32 and a rectangular tool head 33. The piezoelectric transducer 31 is connected to the ultrasonic generator 1, and the piezoelectric transducer 31 is relatively fixed to the ground. The output end of the piezoelectric transducer 31 is fixedly connected to the horn 32. The rectangular tool head 33 is a cube, the output end of the horn 32 is fixedly connected to the rectangular tool head 33, and the first tool head 4 or the second tool head 5 is fixed on the side of the rectangular tool head 33 away from the horn 32.

[0030] In some examples, the piezoelectric transducer 31 is connected to the ultrasonic generator 1, and the piezoelectric transducer 31 receives the vibration from the ultrasonic generator 1, and after power amplification, it emits ultrasonic vibration with greater power. The horn 32 is connected to the piezoelectric transducer 31, and the horn 32 is used to amplify the ultrasonic amplitude. The rectangular tool head can be a block structure and is fixedly connected to the horn 32. For example, the piezoelectric transducer 31 and the horn 32 can be connected by a stud, and the horn 32 and the rectangular tool head 33 can be connected by a stud. The rectangular tool head 33 is fixedly connected to the first tool head 4 or the second tool head 5, for example, the rectangular tool head 33 is fixedly connected to the second tool head 5. The rectangular tool head 33 is used to transmit the ultrasonic vibration from the horn to the first tool head 4 or the second tool head 5.

[0031] In actual applications, the first tool head 4 and the second tool head 5 are adaptively adjusted according to the shape of the aircraft engine blades, that is, multiple types of first tool heads 4 and second tool heads 5 are required. In order to enable the aircraft engine blade inner cavity ultrasonic cleaning device described in the present application to adapt to various types of aircraft engine blades, a rectangular tool head 33 is designed, and the corresponding first tool head 4 or second tool head 5 is assembled to the rectangular tool head 33 according to the type of aircraft engine blades. The first tool head 4 or the second tool head 5 can be fixedly connected to the rectangular tool head 33 using a double-headed stud.

[0032] The rectangular tool head 33 can also evenly distribute the ultrasonic vibration received from the horn to the output end surface of the rectangular tool head 33. After receiving the ultrasonic vibration, the first tool head 4 or the second tool head 5 can provide stable and balanced ultrasonic vibration to the aircraft engine blade.

[0033] In some embodiments, the aircraft engine blade inner cavity ultrasonic cleaning device further includes a bracket 7. The bracket 7 includes: a fixed platform 71, a fixed frame 72 and a movable frame 73. The fixed platform 71 is fixed to the ground, and the fixed platform 71 includes a through slot, one side of the through slot is provided with the at least one first tool head 4, and the other side of the through slot is provided with the at least one second tool head 5. The fixed frame 72 is fixed to the other side of the through slot. The movable frame 73 is fixed to one side of the through slot, and at least one fixed connecting member is provided on the movable frame 73, and the fixed connecting member is configured to fasten the movable frame 73 to the fixed frame 72, and at least one ultrasonic excitation mechanism 3 is fixed on the movable frame 73.

[0034] The movable frame 73 includes: a ball screw and a pressure sensor. At least one ball screw is fixed on the fixed platform 71 on one side of the through slot, and the nut of each ball screw is fixedly connected to a corresponding fixed end 2. A pressure sensor is arranged between each fixed end 2 and the corresponding first tool head 4 or second tool head 5.

[0035] The fixed frame 72 also includes: a vertical truss, a support truss and an adjustment truss. The vertical truss is fixed to the ground. The support truss is fixed to the vertical truss, and the support truss includes at least two parallel support rods, the support rods are straight rods, and grooves are provided on the two support rods. The plane where the center lines of the two support rods are located is perpendicular to the extension direction of the threaded rod of the ball screw. The adjustment truss is arranged on the support truss, and the adjustment truss has a tendency to reciprocate along the support rod. The adjustment truss includes at least two parallel adjustment rods, the adjustment rods are straight rods, and grooves are provided on the two adjustment rods. The plane where the center lines of the two adjustment rods are located is perpendicular to the extension direction of the threaded rod of the ball screw, and the adjustment rod is perpendicular to the support rod, and at least one ultrasonic excitation mechanism 3 is arranged between the adjustment rods.

[0036] The fixing frame 72 further comprises restraining columns. The restraining columns are straight rods, and at least four restraining columns are fixed on the fixing platform 71 around the through slot, and the restraining columns are configured to prevent the object to be cleaned from moving to a range outside the through slot.

[0037] In some examples, the fixing frame 72 may be a metal frame structure, for example, the fixing frame 72 may be made of aluminum alloy profiles, and the fixing frame 72 includes: a vertical truss and a supporting truss, the vertical truss includes four aluminum alloy profiles vertically fixed to the ground, and the supporting truss may be an aluminum alloy rod fixed to both ends of the vertical truss. The fixing frame 72 also includes an adjustment truss, which may be horizontally arranged on the vertical truss, and the adjustment truss may reciprocate in the vertical direction and be fixedly connected to the vertical truss by fastening bolts, and an ultrasonic excitation mechanism.

[0038] A fixed platform 71 is fixed to the top of the vertical truss. The fixed platform 71 is a plate, and a through slot is provided at the upper end of the fixed platform 71. A movable frame 73 is fixed on the fixed platform 71. The lead screw of the ball screw of the movable frame 73 is vertically fixed on the fixed platform 71. The slide of the ball screw is fixedly connected to the fixed end 2. The fixed end 2 can be a block structure similar to the rectangular tool head 33, and is fixedly connected to the first tool head 4 or the second tool head 5. For example, the fixed end 2 can be connected to the first tool head 4 or the second tool head 5 through a stud.

[0039] There is a through slot just below the fixed end and a through slot just above the rectangular tool head 33. The shape of the through slot is adapted to the structure of the first tool head 4 or the second tool head 5 so that the first tool head 4 or the second tool head 5 can pass through the through slot.

[0040] On the other hand, the present invention further provides a method for ultrasonically cleaning the inner cavity of an aircraft engine blade, which is applicable to the ultrasonically cleaning device for cleaning the inner cavity of an aircraft engine blade in the above-mentioned aspect.

[0041] The method for ultrasonic cleaning the inner cavity of an aero-engine blade comprises: S1. Filling wet abrasive particles into the inner cavity of the aircraft engine blade and sealing the inner cavity opening of the aircraft engine blade.

[0042] S2. Fit the first tool head to the outer side wall of the aircraft engine blade, and fit the second tool head to the other outer side wall of the aircraft engine blade, so that the first tool head and the second tool head clamp the aircraft engine blade.

[0043] S3. Control one of the first tool head and the second tool head to generate ultrasonic vibration, and transmit the ultrasonic vibration to the outer side wall of the aircraft engine blade.

[0044] In some examples, the location of the carbon fouling layer in the inner cavity of the aircraft engine blade can be determined by estimation, visual observation from the side opening of the aircraft engine blade, or X-ray detection. Wet abrasive particles are filled into the inner cavity of the aircraft engine blade, and the side opening of the inner cavity of the aircraft engine blade is blocked.

[0045] Then, a plurality of first tool heads and a plurality of second tool heads are attached to the outer surface of the aircraft engine blade. To facilitate the wet abrasive particles to fully clean the inner cavity surface of the aircraft engine blade, the inner side wall to be cleaned can be arranged downward.

[0046] The first tool head or the second tool head performs ultrasonic vibration, and the vibration wave can penetrate the aircraft engine blade into its inner cavity, causing the wet abrasive particles to generate ultrasonic vibration, thereby performing a cleaning operation on the inner cavity of the aircraft engine blade.

[0047] In some embodiments, the method of filling wet abrasive particles into the inner cavity of the aircraft engine blade further comprises: S11, mixing the abrasive particles and the liquid evenly and filling them into the inner cavity of the aero-engine blade.

[0048] S12. The volume of the abrasive particles accounts for 30% to 70% of the inner cavity space of the aircraft engine blade.

[0049] S13. The volume of the liquid occupies 10% to 30% of the inner cavity space of the aero-engine blade.

[0050] Wherein, the abrasive particles are 0.5-2 mm silicon carbide or steel balls, and the liquid is a weak acid solution or water.

[0051] In some embodiments, the method of transmitting ultrasonic vibration to the outer side wall of the aircraft engine blade includes: S31, controlling the ultrasonic frequency of the first tool head or the second tool head to make the side surface corresponding to the aircraft engine blade enter an optimal resonance state.

[0052] S32. Move the one of the first tool head and the second tool head that does not generate ultrasonic vibration closer to the aircraft engine blade to reduce the gap between the one of the first tool head and the second tool head that generates ultrasonic vibration and the aircraft engine blade, until the ultrasonic vibration is microscopically introduced into the inner cavity of the aircraft engine blade.

[0053] The optimal resonance state means that the ultrasonic vibration mode of the first tool head or the second tool head is longitudinal ultrasonic vibration, and the vibration amplitude is the largest.

[0054] In the present application, taking the first tool head generating ultrasonic vibration as an example, during the application process, the vibration state of the first tool head is first adjusted to make the first tool head in the optimal resonance state. At this time, the first tool head is longitudinal ultrasonic vibration, specifically, the first tool head reciprocates in a direction perpendicular to the aircraft engine blades, and the ultrasonic amplitude of the first tool head reaches the maximum.

[0055] The second tool head is gradually pressed toward the aircraft engine blade, so that the macro- and micro-gaps between the first tool head, the second tool head and the surface of the aircraft engine blade are continuously reduced until the high-frequency ultrasonic vibration is effectively introduced into the inner cavity of the aircraft engine blade at the microscopic level, and then the second tool head maintains a constant pressure.

[0056] In some examples, an amplitude measuring instrument is used to measure the ultrasonic amplitude on the surface of an aircraft engine blade. When the ultrasonic amplitude at an excitation position far away from the surface of the aircraft engine blade (on the surface of the aircraft engine blade 10 to 20 cm away from the second tool head) also reaches 5 to 30 μm, the ultrasonic vibration can be effectively introduced into the inner cavity of the surface of the aircraft engine blade.

[0057] After cleaning, the aircraft engine blade is taken out from between the first tool head and the second tool head, and the side opening of the inner cavity is opened to take out the wet abrasive particles and clean them with pure water until the wet abrasive particles are completely discharged from the inner cavity.

[0058] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0059] The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. An ultrasonic cleaning device for the inner cavity of an aircraft engine blade, characterized in that: include: Ultrasonic generator; A fixed end, at least one of which is fixed relative to the ground; An ultrasonic excitation mechanism is provided at a position relative to each fixed end, and the ultrasonic excitation mechanism is connected to the ultrasonic generator; A first tool head, wherein the first tool head comprises a first fitting surface, wherein the first fitting surface of at least one first tool head fits with a surface at a corresponding position of a workpiece to be cleaned, and each first tool head is fixed to a fixed end or an ultrasonic excitation mechanism; A second tool head, wherein the second tool head comprises a second fitting surface, wherein the second fitting surface of at least one second tool head fits with the surface at a corresponding position of the workpiece to be cleaned, and the at least one first tool head and the at least one second tool head clamp the workpiece to be cleaned in the middle, and each second tool head is fixed to a fixed end or an ultrasonic excitation mechanism.

2. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade according to claim 1, characterized in that: A first connecting hole is provided on the side of the first tool head away from the first fitting surface; A second connecting hole is provided on the side of the second tool head away from the second fitting surface; The fixed end includes a fixed connecting piece, one end of which is adapted to the first connecting hole and the second connecting hole, and the fixed end is fixedly connected to the first tool head or the second tool head via the fixed connecting piece.

3. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade according to claim 2, characterized in that: The ultrasonic excitation mechanism comprises: A piezoelectric transducer, the piezoelectric transducer is connected to the ultrasonic generator, and the piezoelectric transducer is fixed relative to the ground; A horn, the output end of the piezoelectric transducer is fixedly connected to the horn; A rectangular tool head is a cube, the output end of the amplitude changing rod is fixedly connected to the rectangular tool head, and the first tool head or the second tool head is fixed to a side of the rectangular tool head away from the amplitude changing rod.

4. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade according to claim 3, characterized in that: The aero-engine blade inner cavity ultrasonic cleaning device also includes a bracket; The support comprises: A fixed platform, the fixed platform is fixed to the ground, the fixed platform comprises a through slot, one side of the through slot is provided with the at least one first tool head, and the other side of the through slot is provided with the at least one second tool head; A fixing frame, the fixing frame being fixed to the other side of the through slot; A movable frame is fixed to one side of the through slot, at least one fixed connecting member is arranged on the movable frame, the fixed connecting member is configured to fasten the movable frame to the fixed frame, and at least one ultrasonic excitation mechanism is fixed on the movable frame.

5. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade according to claim 4, characterized in that: The mobile frame comprises: A ball screw, at least one ball screw is fixed to a fixed platform on one side of the through slot, and a nut of each ball screw is fixedly connected to a corresponding fixed end; A pressure sensor is provided between each fixed end and the corresponding first tool head or second tool head.

6. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade according to claim 5, characterized in that: The fixing frame also includes: A vertical truss, wherein the vertical truss is fixed to the ground; A support truss, the support truss is fixed on the vertical truss, the support truss comprises at least two support rods arranged in parallel, the support rods are straight rods, grooves are arranged on the two support rods, and the plane where the center lines of the two support rods are located is perpendicular to the extension direction of the threaded rod of the ball screw; An adjustment truss, wherein the adjustment truss is arranged on the support truss, and the adjustment truss has a tendency to reciprocate along the support rod, the adjustment truss includes at least two parallel adjustment rods, the adjustment rods are straight rods, grooves are arranged on the two adjustment rods, the plane where the center lines of the two adjustment rods are located is perpendicular to the extension direction of the threaded rod of the ball screw, and the adjustment rods are perpendicular to the support rods, and at least one ultrasonic excitation mechanism is arranged between the adjustment rods.

7. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade according to claim 6, characterized in that: The fixing frame also includes a restraining column; The restraining columns are straight rods, and at least four restraining columns are fixed on a fixing platform around the through slot. The restraining columns are configured to prevent the object to be cleaned from moving to a range outside the through slot.

8. An ultrasonic cleaning method for the inner cavity of an aircraft engine blade, applicable to the ultrasonic cleaning device for the inner cavity of an aircraft engine blade as claimed in any one of claims 1 to 7, characterized in that: The method for ultrasonic cleaning the inner cavity of an aero-engine blade comprises: Filling wet abrasive particles into the inner cavity of the aero-engine blade and sealing the inner cavity opening of the aero-engine blade; Fitting the first tool head to the outer side wall of the aircraft engine blade, and fitting the second tool head to the other outer side wall of the aircraft engine blade, so that the first tool head and the second tool head clamp the aircraft engine blade; One of the first tool head and the second tool head is controlled to generate ultrasonic vibration, and the ultrasonic vibration is transmitted to the outer side wall of the aircraft engine blade.

9. The method for ultrasonic cleaning of the inner cavity of an aircraft engine blade according to claim 8, characterized in that: The method of filling wet abrasive particles into the inner cavity of the aero-engine blade further comprises: The abrasive particles and the liquid are mixed and stirred evenly and filled into the inner cavity of the aero-engine blade, The volume of the abrasive particles accounts for 30% to 70% of the inner cavity space of the aero-engine blade. The volume of the liquid accounts for 10% to 30% of the inner cavity space of the aero-engine blade; Wherein, the abrasive particles are 0.5-2 mm silicon carbide or steel balls, and the liquid is a weak acid solution or water.

10. The method for ultrasonic cleaning of the inner cavity of an aircraft engine blade according to claim 9, characterized in that: The method of transmitting ultrasonic vibration to the outer side wall of the aeroengine blade comprises: Controlling the ultrasonic frequency of the first tool head or the second tool head so that the side surface corresponding to the aeroengine blade enters an optimal resonance state; The one of the first tool head and the second tool head that does not generate ultrasonic vibration is brought closer to the aircraft engine blade, so that the gap between the one of the first tool head and the second tool head that generates ultrasonic vibration and the aircraft engine blade is reduced until the ultrasonic vibration is introduced into the inner cavity of the aircraft engine blade at a microscopic level; The optimal resonance state means that the ultrasonic vibration mode of the first tool head or the second tool head is longitudinal ultrasonic vibration, and the vibration amplitude is the largest.

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