Ultrasonic cleaning device and method for inner cavity of aircraft engine blades

Abstract

The application belongs to the field of ultrasonic cleaning and relates to an aero-engine blade inner cavity ultrasonic cleaning device and method. The device can produce ultrasonic vibration on the blade and excite cavitation and abrasive of the blade inner cavity, thereby realizing efficient and high-quality cleaning of the blade inner cavity deposits. The technical scheme comprises an ultrasonic generator, a fixed end, an ultrasonic excitation mechanism, a first tool head and a second tool head. The fixed end is relatively fixed to the ground. The ultrasonic excitation mechanism is arranged at a relative position of the fixed end and connected to the ultrasonic generator. The first tool head comprises a first abutting surface which is abutted to the surface at the corresponding position of the workpiece to be cleaned, and the first tool head is fixed to the fixed end or the ultrasonic excitation mechanism. The second tool head comprises a second abutting surface which is abutted to the surface at the corresponding position of the workpiece to be cleaned, and the first tool head and the second tool head clamp the workpiece to be cleaned to the middle, and the second tool head is fixed to the fixed end or the ultrasonic excitation mechanism.

Description

TECHNICAL FIELD

[0001] The application 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. BACKGROUND

[0002] An aero-engine blade is operated in a harsh working environment for a long time and faces challenges of high temperature, high pressure and high strain load. Aviation fuel and its combustion products can deposit in the inner cavity of the blade to form a hard and brittle carbon scale layer. The carbon scale layer can block the internal cooling channel of the blade, seriously reduce the cooling efficiency and service life of the blade, and pose a potential threat to the safety performance of the aero-engine, and therefore must be completely removed.

[0003] At present, the cleaning methods for the inner cavity deposits of the blade mainly include manual cleaning, solvent soaking and ultrasonic cleaning. However, the manual cleaning has low efficiency and high cost, and the solvent soaking is almost ineffective for thick deposits. In the ultrasonic cleaning method, the traditional ultrasonic cavitation effect has limited cleaning effect due to the complex flow channel of the inner cavity of the blade. Other methods such as liquid-free focused ultrasonic cleaning (CN103128081A) remove the inner cavity deposits by inducing vibration of the blade tenon through the focused ultrasonic wave acting on the blade tenon position, but the energy is greatly lost in the propagation process of the ultrasonic wave from the blade tenon to the blade body, and the inner cavity deposits far from the blade tenon are not completely removed. In addition, there is an embedded contact type micro-hole ultrasonic cleaning method, which clamps both ends of the blade, uses ultrasonic excitation metal sand to remove the inner cavity deposits, but the method has poor effect on the removal of deposits in specific areas.

[0004] Based on the above problems, the application provides an ultrasonic excitation wet abrasive cleaning device for inner cavity deposits of an aero-engine blade, which can generate strong ultrasonic vibration at any local position of the blade and excite cavitation and abrasive in the inner cavity of the blade to realize efficient and high-quality cleaning of the inner cavity deposits of the blade. SUMMARY

[0005] To overcome the defects in the related art, on the one hand, the application provides an ultrasonic cleaning device for an inner cavity of an aero-engine blade, which can generate strong ultrasonic vibration at any local position of the blade and excite cavitation and abrasive in the inner cavity of the blade to realize efficient and high-quality cleaning of the inner cavity deposits of the blade.

[0006] To achieve the above technical purposes, the present application provides an aero-engine blade inner cavity ultrasonic cleaning device. The aero-engine blade inner cavity ultrasonic cleaning device 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 relatively fixed to the ground. An ultrasonic excitation mechanism is arranged at a relative position of each fixed end, and the ultrasonic excitation mechanism is connected with the ultrasonic generator. The first tool head comprises a first fitting surface, the first fitting surface of at least one first tool head is fitted with 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, the second fitting surface of at least one second tool head is fitted with 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 connecting hole is arranged on the side of the first tool head away from the first fitting surface. A second connecting hole is arranged on the side of the second tool head away from the second fitting surface. The fixed end comprises a fixed connecting piece, one end of the fixed connecting piece is adapted to the first connecting hole and the second connecting hole, and the fixed end is fixedly connected with the first tool head or the second tool head through the fixed connecting piece.

[0008] Preferably, the ultrasonic excitation mechanism comprises a piezoelectric transducer, an amplitude transformer and a rectangular tool head. The piezoelectric transducer is connected with the ultrasonic generator, and the piezoelectric transducer is relatively fixed to the ground. The output end of the piezoelectric transducer is fixedly connected with the amplitude transformer. The rectangular tool head is a square, the output end of the amplitude transformer is fixedly connected with the rectangular tool head, and the rectangular tool head is fixed with the first tool head or the second tool head on the side away from the amplitude transformer.

[0009] Preferably, the aero-engine blade inner cavity ultrasonic cleaning device further comprises a support. The support comprises a fixed table, a fixed frame and a moving frame. The fixed table is fixed to the ground, and the fixed table 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. The fixed frame is fixed to the other side of the through slot. The moving frame is fixed to one side of the through slot, and the moving frame is provided with at least one fixed connecting piece configured to fasten the moving frame and the fixed frame, and the moving frame is fixed with at least one ultrasonic excitation mechanism.

[0010] Preferably, the moving frame comprises a ball screw and a pressure sensor. At least one ball screw is fixed on the fixed table on one side of the through slot, and the nut of each ball screw is fixedly connected with 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 comprises 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 comprises at least two parallel support rods. The support rods are straight rods, and grooves are arranged on the two support rods. The plane in which the center lines of the two support rods lie 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 rods. The adjustment truss comprises at least two parallel adjustment rods. The adjustment rods are straight rods, and grooves are arranged on the two adjustment rods. The plane in which the center lines of the two adjustment rods lie is perpendicular to the extension direction of the threaded rod of the ball screw, and the adjustment rods are perpendicular to the support rods. At least one ultrasonic excitation mechanism is arranged between the adjustment rods.

[0012] Preferably, the fixed frame further comprises a constraint column. The constraint column is a straight rod, and at least four constraint columns are fixed on the fixed table around the through slot. The constraint columns are configured to prevent the to-be-cleaned piece from moving to a range outside the through slot.

[0013] In another aspect, the present application also provides an aero-engine blade inner cavity ultrasonic cleaning method suitable for the aero-engine blade inner cavity ultrasonic cleaning device in the above-mentioned aspect. The aero-engine blade inner cavity ultrasonic cleaning method comprises: filling wet abrasive particles into the aero-engine blade inner cavity, and plugging the aero-engine blade inner cavity opening. The first tool head is attached to the outer side wall of the aero-engine blade, and the second tool head is attached to the other outer side wall of the aero-engine blade, so that the first tool head and the second tool head clamp the aero-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 aero-engine blade.

[0014] Preferably, the method of filling wet abrasive particles into the aero-engine blade inner cavity further comprises: uniformly mixing and stirring the abrasive particles and the liquid, and filling them into the aero-engine blade inner cavity. The volume of the abrasive particles accounts for 30% to 70% of the space of the aero-engine blade inner cavity. The volume of the liquid accounts for 10% to 30% of the space of the aero-engine blade inner cavity. 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 vibrations to the outer sidewall of the aircraft engine blade includes: controlling the ultrasonic frequency of the first tool head or the second tool head to bring the corresponding side of the aircraft engine blade into an optimal resonant state. The first or second tool head that does not generate ultrasonic vibrations is brought closer to the aircraft engine blade, thereby reducing the gap between the first or second tool head that generates ultrasonic vibrations and the aircraft engine blade, until the ultrasonic vibrations are microscopically introduced into the inner cavity of the aircraft engine blade. The optimal resonant state refers to the ultrasonic vibration mode of the first or second tool head being longitudinal ultrasonic vibration, with the vibration amplitude being maximum.

[0016] The beneficial effects of the present invention are:

[0017] The present invention adopts a first tool head and a second tool head, which are arranged in a fit manner with the aircraft engine blade to transmit ultrasonic vibrations to the interior of the aircraft engine blade, thereby completing the cleaning work of the interior of the aircraft engine blade with abrasive particles. In this way, 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

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the following briefly introduces the drawings required for use in the embodiments or related technical descriptions. 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 any creative work.

[0019] Figure 1 A structural diagram of the present invention;

[0020] Figure 2 Another structural diagram of the present invention;

[0021] Figure 3 is a structural diagram of a first tool head of the present invention;

[0022] Figure 4 is a structural diagram of a second tool head of the present invention;

[0023] Figure 5 is a structural diagram of the ultrasonic excitation mechanism and the first tool head of the present invention;

[0024] Figure 6 A structural diagram of the ultrasonic excitation mechanism and the second tool head of the present invention;

[0025] Figure 7 This is another structural diagram of the present invention;

[0026] Figure 8It is a structural diagram of the fixing platform and fixing frame of the present invention;

[0027] Figure 9 A working state diagram of a plurality of first tool heads and a plurality of second tool heads of the present invention;

[0028] Figure 10 This is another working state diagram of the multiple first tool heads and the multiple second tool heads of the present invention. DETAILED DESCRIPTION

[0029] To make the above-mentioned objects, features, and advantages of the present invention more clearly understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0030] 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 accompanying 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 limiting the present invention.

[0031] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0032] like Figures 1 to 10As 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 provided at a position relative to each fixed end 2, and the ultrasonic excitation mechanism 3 is connected to the ultrasonic generator 1. The first tool head 4 includes a first bonding surface 41. The first bonding surface 41 of at least one first tool head 4 is bonded to the surface of a corresponding position of a workpiece 6 to be cleaned. Each first tool head 4 is fixed to a fixed end 2 or an ultrasonic excitation mechanism 3. The second tool head 5 includes a second bonding surface 51. The second bonding surface 51 of at least one second tool head 5 is bonded to the surface of a corresponding position of the workpiece 6 to be cleaned. The at least one first tool head 4 and the at least one second tool head 5 clamp the workpiece 6 to be cleaned in the middle. Each second tool head 5 is fixed to a fixed end 2 or an ultrasonic excitation mechanism 3.

[0033] In some examples, the fixed end 2 and the ultrasonic excitation mechanism 3 are arranged opposite 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. The first tool head 4 is fixed to the end of the fixed end 2 facing the ultrasonic excitation mechanism 3, and the second tool head 5 is fixed to the end of the ultrasonic excitation mechanism 3 facing the fixed end 2. 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.

[0034] A part to be cleaned, such as an aircraft engine blade, is clamped between the first tool head 4 and the second tool head 5. The aircraft engine blade can be a hollow blade. During combustion within the aircraft engine, a carbon scale layer is deposited in the blade's inner cavity. Abrasive and cleaning fluid can be poured into the inner cavity of the aircraft engine blade, and the open end of the inner cavity of the aircraft engine blade is sealed. Multiple second tool heads 5 are attached to the outer surface of the aircraft engine blade to transmit ultrasonic vibrations to the aircraft engine blade, thereby causing the cleaning fluid and abrasive in the inner cavity of the aircraft engine blade to ultrasonically vibrate, thereby sequentially cleaning the carbon scale layer deposited in the inner cavity of the aircraft engine blade.

[0035] The present application can transmit ultrasonic vibrations to the inner cavity through the outer surface of the aircraft engine blade, and can 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.

[0036] 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 fit into the first and second connection holes, and the fixed end 2 is fixedly connected to the first tool head 4 or the second tool head 5 via the fixed connector.

[0037] In some examples, the first tool head 4 can be a block-shaped structure, and a first fitting surface 41 is provided on the first tool head 4. The first fitting surface 41 can be adapted to the outer protruding curved surface of the aircraft engine blade, that is, the first fitting surface 41 can be closely fitted with the outer protruding curved surface of the aircraft engine blade. Similarly, the second tool head 5 can be a block-shaped structure, and a second fitting surface 51 is provided on the second tool head 5. The second fitting surface 51 can be adapted to the outer protruding curved surface of the aircraft engine blade, that is, the second fitting surface 51 can be closely fitted with the outer protruding curved surface of the aircraft engine blade.

[0038] Multiple second tool heads 5 can be attached to an aircraft engine blade, where the corresponding inner cavity of the aircraft engine blade to which the multiple second tool heads 5 are attached has a carbon scale layer. Multiple first tool heads 4 are attached to the aircraft engine blade and positioned opposite the multiple second tool heads 5. The ultrasonic generator 1 is activated, ultrasonically vibrating the multiple second tool heads 5. The multiple second tool heads 5 transmit the ultrasonic vibrations through the aircraft engine blade into its inner cavity, causing the cleaning fluid and abrasive to generate ultrasonic vibrations, thereby cleaning the carbon scale layer at that location. Similarly, carbon scale layers at other locations within the inner cavity of the aircraft engine blade can be cleaned using the above method.

[0039] 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 fixed relative 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, and the output end of the horn 32 is fixedly connected to the rectangular tool head 33. The first tool head 4 or the second tool head 5 is fixed to the side of the rectangular tool head 33 away from the horn 32.

[0040] 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 emits ultrasonic vibrations with higher power after power amplification. 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 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 ultrasonic vibrations from the horn to the first tool head 4 or the second tool head 5.

[0041] In actual application, the first tool head 4 and the second tool head 5 are adaptively adjusted according to the shape of the aircraft engine blade, 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 this 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 blade. 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.

[0042] The rectangular tool head 33 can also evenly distribute the ultrasonic vibration received from the horn on 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.

[0043] In some embodiments, the ultrasonic cleaning device for the inner cavity of an aircraft engine blade 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.

[0044] The movable frame 73 includes a ball screw and a pressure sensor. At least one ball screw is fixed to a fixed platform 71 on one side of the through slot. The nut of each ball screw is fixedly connected to a corresponding fixed end 2. A pressure sensor is installed between each fixed end 2 and the corresponding first tool head 4 or second tool head 5.

[0045] 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, which are straight rods with grooves 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. The adjustment truss includes at least two parallel adjustment rods, which are straight rods with grooves 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. At least one ultrasonic excitation mechanism 3 is provided between the adjustment rods.

[0046] The fixing frame 72 further includes 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. The restraining columns are configured to prevent the items to be cleaned from moving outside the through slot.

[0047] In some examples, the fixing frame 72 may be a metal frame structure, such as an aluminum alloy profile. The fixing frame 72 includes a vertical truss and a support truss. The vertical truss includes four aluminum alloy profiles vertically fixed to the ground, and the support truss may be aluminum alloy rods fixed to both ends of the vertical truss. The fixing frame 72 also includes an adjustment truss, which can be horizontally arranged on the vertical truss. The adjustment truss can reciprocate in the vertical direction and is fixedly connected to the vertical truss by fastening bolts, thereby forming an ultrasonic excitation mechanism.

[0048] A fixed platform 71 is fixed to the top of the vertical truss. The fixed platform 71 is a plate with a through slot at its upper end. A movable frame 73 is fixed to the fixed platform 71. The ball screw of the movable frame 73 is vertically fixed to the fixed platform 71. The ball screw slide is fixedly connected to the fixed end 2. The fixed end 2 can be a block-shaped 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 via a stud.

[0049] There is a through slot just below the fixed end and 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.

[0050] 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 aspect.

[0051] The ultrasonic cleaning method for the inner cavity of an aero-engine blade comprises:

[0052] S1. Filling wet abrasive particles into the inner cavity of the aero-engine blade and sealing the inner cavity opening of the aero-engine blade.

[0053] 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.

[0054] 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.

[0055] In some examples, the location of the carbon fouling layer within the inner cavity of an aircraft engine blade can be determined by estimation, visual inspection through a side opening of the aircraft engine blade, or X-ray inspection. The inner cavity of the aircraft engine blade is then filled with wet abrasive particles, and the side opening of the inner cavity of the aircraft engine blade is sealed.

[0056] Then, multiple first tool heads and multiple second tool heads are attached to the outer surface of the aircraft engine blade. In order 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 placed downward.

[0057] 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 aircraft engine blade inner cavity.

[0058] In some embodiments, the method of filling the inner cavity of the aircraft engine blade with wet abrasive particles further comprises:

[0059] S11, mixing the abrasive particles and the liquid evenly and filling the mixture into the inner cavity of the aero-engine blade.

[0060] S12. The volume of the abrasive particles occupies 30% to 70% of the inner cavity space of the aero-engine blade.

[0061] S13. The volume of the liquid occupies 10% to 30% of the inner cavity space of the aero-engine blade.

[0062] Wherein, the abrasive particles are 0.5-2 mm silicon carbide or steel balls, and the liquid is a weak acid solution or water.

[0063] In some embodiments, the method of transmitting ultrasonic vibrations to the outer sidewall of the aircraft engine blade includes:

[0064] S31. Control the ultrasonic frequency of the first tool head or the second tool head to bring the corresponding side surface of the aircraft engine blade into an optimal resonance state.

[0065] S32. Move the one of the first tool head and the second tool head that does not generate ultrasonic vibrations 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 vibrations and the aircraft engine blade is reduced, until the ultrasonic vibrations are microscopically introduced into the inner cavity of the aircraft engine blade.

[0066] 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.

[0067] 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 so that the first tool head is 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.

[0068] The second tool head is gradually pressed toward the aircraft engine blade, so that the macro- and microscopic gaps between the first and second tool heads and the surface of the aircraft engine blade are continuously reduced until high-frequency ultrasonic vibrations are effectively introduced into the inner cavity of the aircraft engine blade at the microscopic level, after which the second tool head maintains constant pressure.

[0069] In some examples, an amplitude meter 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.

[0070] After cleaning, the aircraft engine blade is removed 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.

[0071] 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.

[0072] The above are only specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this invention should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection 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 opposite to each fixed end, and the ultrasonic excitation mechanism is connected to the ultrasonic generator; a first tool head, the first tool head comprising a first fitting surface, the first fitting surface of at least one first tool head fitting against a surface of a corresponding position of a workpiece to be cleaned, each first tool head being fixed to a fixed end or an ultrasonic excitation mechanism; a second tool head, the second tool head including a second fitting surface, the second fitting surface of at least one second tool head fitting against a surface of a corresponding position of a workpiece to be cleaned, and the at least one first tool head and the at least one second tool head clamping the workpiece to be cleaned between them, each second tool head being fixed to a fixed end or an ultrasonic excitation mechanism; The method for using the ultrasonic cleaning device for the inner cavity of an aircraft 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 a first tool head to an outer side wall of the aircraft engine blade, and fitting a second tool head to another outer side wall of the aircraft engine blade, so that the first tool head and the second tool head clamp the aircraft engine blade; controlling 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; The method of transmitting ultrasonic vibration to the outer side wall of the aero-engine blade comprises: controlling the ultrasonic frequency of the first tool head or the second tool head so that the corresponding side surface of the aircraft engine blade enters an optimal resonance state; moving the one of the first and second tool heads that does not generate ultrasonic vibrations closer to the aircraft engine blade to reduce the gap between the one of the first and second tool heads that generates ultrasonic vibrations and the aircraft engine blade until the ultrasonic vibrations are microscopically introduced into the inner cavity of the aircraft engine blade; 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.

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 connector, 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 connector.

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 includes: a piezoelectric transducer, the piezoelectric transducer being connected to the ultrasonic generator and being fixed relative to the ground; A horn, to which the output end of the piezoelectric transducer is fixedly connected; 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 further comprises a bracket; The bracket comprises: a fixed platform, the fixed platform being fixed to the ground, the fixed platform comprising a through slot, the at least one first tool head being disposed on one side of the through slot, and the at least one second tool head being disposed on the other side of the through slot; a fixing frame 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 provided 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; Pressure sensor: 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 further comprises: A vertical truss, wherein the vertical truss is fixed to the ground; A support truss, the support truss being fixed to the vertical truss, the support truss comprising at least two parallel support rods, the support rods being straight rods, the two support rods being provided with grooves, the plane where the center lines of the two support rods lie being perpendicular to the extension direction of the threaded rod of the ball screw; An adjustment truss is provided 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 rods are perpendicular to the support rods. At least one ultrasonic excitation mechanism is provided 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 further 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 items to be cleaned from moving to a range outside the through slot.

8. The ultrasonic cleaning device for the inner cavity of an aircraft engine blade according to claim 7, characterized in that: The method of filling the inner cavity of the aero-engine blade with wet abrasive particles further comprises: The abrasive particles and the liquid are mixed and stirred evenly and then filled into the inner cavity of the aero-engine blade. The volume of the abrasive particles occupies 30% to 70% of the inner cavity space of the aero-engine blade. The volume of the liquid occupies 10% to 30% of the inner cavity space of the aero-engine blade; The abrasive particles are 0.5-2 mm silicon carbide or steel balls, and the liquid is a weak acid solution or water.

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