Automatic detection production line and aviation blade core detection method

Abstract

The invention belongs to the field of aperture detection, and particularly relates to an automatic detection production line and an aviation blade core detection method, and the automatic detection production line comprises a control module, a detection base, a sound intensity receiving assembly, a ventilation assembly, a feeding assembly, a material moving assembly and a bottomless bearing disc; the sound intensity receiving assembly is suitable for receiving sound intensity value information when gas blows through a through hole of a mold core of the aviation blade and sending the sound intensity value information to the control module; and the control module is suitable for detecting the through hole of the mold core of the aviation blade according to the sound intensity value information. According to the characteristic that sound intensity values generated when airflow passes through different apertures are different, a related mechanical detection structure is designed, meanwhile, the surface of the mold core is cleaned through the airflow, the influence of sweeps on detection is avoided, and therefore accurate detection on the surfaces of the through holes of the mold core and the connecting blocks between the through holes is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of aperture detection, and specifically relates to a mechanical measuring instrument, and in particular to an automated detection production line and a core detection method for aviation blades. Background Art

[0002] Aircraft blades are formed by placing four cores into a wax injection mold. When preparing the core, the investment casting technology is adopted, that is, the binder and ceramic material are mixed and injected into the mold to obtain the core. The core is hardened after firing, and the preparation of the core is completed. After preparation, the core needs to be trimmed and tested.

[0003] In the related art, manual trimming is used. After the trimming is completed, the core is manually placed in a visual inspection mechanism to inspect the through-hole diameter of the core and the surface of the connecting block between the through-holes. However, when there are scraps on the surface of the core, the image information obtained by the visual inspection mechanism has errors, resulting in misdetection. At the same time, when there are depressions on the inner wall of the through-hole, it cannot be detected by the visual inspection mechanism.

[0004] Therefore, how to clean and accurately detect the diameter of the through holes of the core of the aircraft blade and the surface of the connecting blocks between the through holes is a technical problem that needs to be solved urgently.

[0005] It should be noted that the above information disclosed in this background technology section is only used to understand the background technology of the present application concept, and therefore, the above description is not considered to constitute information of the prior art. Summary of the invention

[0006] The embodiments of the present disclosure at least provide an automated inspection production line and a core inspection method for aircraft blades.

[0007] In a first aspect, an embodiment of the present disclosure provides an automated detection production line, including: Control module, detection base, sound intensity receiving component, ventilation component, feeding component, material moving component and bottomless tray; The detection base is arranged on the discharge side of the feeding assembly; The sound intensity receiving component is arranged on the detection base; The ventilation assembly is arranged above the detection base; The detection base is provided with a detection slit; The bottomless tray carries a core of an aviation blade to be inspected; The material transfer assembly is adapted to move the bottomless tray conveyed by the material feeding assembly to the detection base, and to move the through hole of the core of the aviation blade in the bottomless tray to between the ventilation assembly and the detection slit; The sound intensity receiving component is adapted to receive sound intensity value information when gas blows through the through hole of the core of the aviation blade, and send the sound intensity value information to the control module; The control module is suitable for detecting the through hole of the core of the aviation blade according to the sound intensity value information.

[0008] In an optional embodiment, the control module stores preset sound intensity values ​​of the core of a qualified aviation blade after through-hole ventilation; The control module is configured to compare the received sound intensity value information with a preset sound intensity value, thereby completing the detection of the through hole of the core of the aviation blade.

[0009] In an optional embodiment, the sound intensity receiving component includes: at least two sound detection modules; The control module is electrically connected to the two sound detection modules respectively.

[0010] In an optional embodiment, the control module is configured to compare the two sets of received sound intensity value information with the corresponding preset sound intensity values ​​respectively. When any one of the two sets of sound intensity value information does not match the preset sound intensity values, the through hole of the core of the aviation blade is unqualified, otherwise, it is qualified.

[0011] In an optional embodiment, the ventilation assembly includes: an air pump and a ventilation box; The air pump is in communication with the ventilation box; The bottom surface of the ventilation box is provided with an air outlet; The position of the air outlet is adapted to the detection slit, that is, the gas from the air pump enters the ventilation box and is blown into the detection slit through the air outlet.

[0012] In an optional embodiment, two side walls of the air outlet are respectively bonded with sealing lips; The two sealing lips are suitable for opening the air outlet when gas is introduced into the ventilation box; The two sealing lips are also suitable for closing the air outlet when the air pump extracts the gas in the ventilation box, so as to detect the air tightness of the ventilation box.

[0013] In an optional embodiment, the ventilation assembly further includes a connecting frame and a lifting cylinder; The lifting cylinder is fixed on the detection base through a connecting frame; The ventilation box is fixedly arranged on the piston rod of the lifting cylinder and is suitable for lifting and lowering under the drive of the lifting drive unit, so that the ventilation box is close to the bottomless support tray and the two sealing lips are abutted against both sides of the through hole of the core of the aviation blade.

[0014] In an optional embodiment, the bottom surface of the ventilation box is provided with a snap ring adapted to the bottomless support tray.

[0015] In an optional embodiment, the clamping ring is slidably arranged on the bottom surface of the ventilation box.

[0016] In a second aspect, the present disclosure also provides an automated detection production line, including: Control module, detection base, sound intensity receiving component, ventilation component, discharging component, material transfer component and bottomless tray; The detection base is arranged on the feeding side of the discharging assembly; The sound intensity receiving component is arranged on the detection base; The ventilation assembly is arranged above the detection base; The detection base is provided with a detection slit; The bottomless tray carries a core of an aviation blade to be inspected; The sound intensity receiving component is adapted to receive sound intensity value information when gas blows through the through hole of the core of the aviation blade, and send the sound intensity value information to the control module; The control module is suitable for detecting the through holes of the core of the aircraft blade according to the sound intensity value information, and controlling the material transfer component to transport the inspected core of the aircraft blade to the corresponding conveying area of ​​the discharging component according to the detection result.

[0017] In a third aspect, an embodiment of the present disclosure further provides a method for detecting a core of an aircraft blade, the method being suitable for detecting a core of an aircraft blade conveyed by the above-mentioned automated detection production line, the method comprising: Control the material transfer assembly to move the bottomless tray onto the detection base; Controlling the ventilation assembly to ventilate the through holes of the core of the aviation blade on the seamless tray; The sound intensity value information when the gas blows through the through hole of the core of the aviation blade is received by the sound intensity receiving component; The detection of the through hole of the core of the aviation blade is completed based on the sound intensity value information.

[0018] The beneficial effect of the present invention is that the automated inspection production line and the core inspection method for aviation blades ventilate the through holes of the core through the ventilation components, clean the surface of the core and the inside of the through holes by the gas, and at the same time, receive the sound made when the gas blows through the through holes of the core of the aviation blade to judge whether the diameter of the through holes of the core is qualified and whether the inner walls of the through holes have defects. The core is first cleaned with gas to avoid the influence of waste chips on the inspection process, thereby accurately inspecting the through holes of the core.

[0019] Other features and advantages of the present invention will be described in the following description, and partly become apparent from the description, or understood by practicing the present invention. The purpose and other advantages of the present invention are realized and obtained by the structures particularly pointed out in the description, claims and drawings.

[0020] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, this article specifically cites preferred embodiments and provides detailed descriptions as follows in conjunction with the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 A three-dimensional diagram of an automated inspection production line provided in an embodiment of the present disclosure; Figure 2 A schematic diagram of a partial structure of an automated inspection production line provided in an embodiment of the present disclosure; Figure 3 A schematic structural diagram of the ventilation box provided in an embodiment of the present disclosure.

[0023] Figure 4 A cross-sectional view of a ventilation box provided in accordance with an embodiment of the present disclosure.

[0024] Figure 5 Bottom view of a ventilation box provided for an embodiment of the present disclosure.

[0025] Figure 6 It is a three-dimensional diagram of the partial structure of the automated inspection production line provided in an embodiment of the present disclosure.

[0026] In the figure: In the figure: 100, detection base; 110, detection slit; 200, sound intensity receiving component; 300, ventilation component; 310, ventilation box; 311, air outlet; 312, sealing lip; 313, retaining ring; 320, connecting frame; 330, lifting cylinder; 400, feeding component; 500, material moving component; 600, bottomless tray; 700, discharging component; 710, first discharging channel; 720, second discharging channel; 730, switching plate. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are 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 are within the scope of protection of the present invention.

[0028] In this article, when it is mentioned that the first component is located on the second component, this may mean that the first component may be directly formed on the second component, or the third component may be interposed between the first component and the second component. In addition, in the drawings, in order to effectively describe the technical content, the thickness of the components may be exaggerated or reduced.

[0029] Herein, example embodiments of the present disclosure will be described in more detail with reference to the accompanying drawings. As used herein, expressions such as "at least one of..." modify the entire list of elements when following a list of elements, rather than modifying individual elements in the list. For example, the expression "at least one of a, b, and c" should be understood to include only a, only b, only c, both a and b, both a and c, both b and c, or all of a, b, and c.

[0030] As used herein, the phrases "in one embodiment," "according to one embodiment," "in some embodiments," and the like generally refer to the fact that the particular feature, structure, or characteristic following the phrase may be included in at least one embodiment of the present disclosure. Therefore, a particular feature, structure, or characteristic may be included in more than one embodiment of the present disclosure, so that these phrases do not necessarily refer to the same embodiment. As used herein, the terms "example," "exemplary," and the like are used to "serve as an example, instance, or illustration." Any implementation, aspect, or design described herein as "example" or "exemplary" is not necessarily to be construed as preferred or superior to other implementations, aspects, or designs. On the contrary, the use of the terms "example," "exemplary," and the like is intended to present concepts in a concrete manner.

[0031] Research has found that when using visual inspection to inspect the core, on the one hand, when there is waste on the surface of the core, the image information obtained by the visual inspection mechanism will be inaccurate, resulting in misdetection. On the other hand, when there is a depression on the inner wall of the through hole, it cannot be inspected by the visual inspection mechanism. Therefore, how to clean and accurately inspect the through hole diameter of the core of the aviation blade and the surface of the connecting block between the through holes is currently an urgent problem to be solved.

[0032] Based on the above research, the embodiments of the present disclosure provide an automated inspection production line and a core inspection method for aviation blades. According to the characteristics of different sound intensity values ​​emitted when the airflow passes through different apertures, a related mechanical inspection structure is designed. At the same time, the surface of the core is cleaned by the airflow to avoid the influence of waste chips on the inspection, thereby achieving accurate inspection of the through holes of the core and the surfaces of the connecting blocks between the through holes.

[0033] Some embodiments of the present invention are described in detail below in conjunction with the accompanying drawings. In the absence of conflict, the following embodiments and features in the embodiments can be combined with each other.

[0034] See also Figure 1 and Figure 2 , Figure 1 The automatic detection production line is shown, including: a control module, a detection base 100, a sound intensity receiving component 200, a ventilation component 300, a feeding component 400, a material moving component 500 and a bottomless tray 600; the detection base 100 is arranged on the discharge side of the feeding component 400; the sound intensity receiving component 200 is arranged on the detection base 100; the ventilation component 300 is arranged above the detection base 100; the detection base 100 is provided with a detection slit 110; the bottomless tray 600 carries the material to be detected. The core of the aviation blade; the material moving assembly 500 is suitable for moving the bottomless tray 600 conveyed by the feeding assembly 400 to the detection base 100, and moving the through hole of the core of the aviation blade in the bottomless tray 600 to between the ventilation assembly 300 and the detection slit 110; the sound intensity receiving assembly 200 is suitable for receiving the sound intensity value information when the gas blows through the through hole of the core of the aviation blade, and sending the sound intensity value information to the control module; the control module is suitable for detecting the through hole of the core of the aviation blade according to the sound intensity value information. The through hole of the core is ventilated through the ventilation assembly 300, and the surface and the inside of the through hole of the core are cleaned by gas. At the same time, by receiving the sound emitted when the gas blows through the through hole of the core of the aviation blade, it is judged whether the diameter of the through hole of the core is qualified and whether the inner wall of the through hole is defective, and the core is first cleaned by gas to avoid the influence of waste chips on the detection process, so as to accurately detect the through hole of the core.

[0035] On the other hand, after the gas passes through the through hole of the core of the aviation blade and then passes through the detection slit 110, a narrow tube effect is formed, so that the gas passes through the detection slit 110 and accelerates because it cannot accumulate in large quantities, causing the wind speed to increase instantly, thereby increasing the loudness and making it easier for the sound intensity receiving component 200 to collect sound intensity value information.

[0036] Specifically, the control module stores preset sound intensity values ​​of the through holes of the core of a qualified aviation blade after ventilation; the control module is configured to compare the received sound intensity value information with the preset sound intensity value, thereby completing the detection of the through holes of the core of the aviation blade.

[0037] The preset sound intensity value is obtained by performing multiple tests on qualified cores, removing impurities after obtaining the sound intensity value information, and averaging the remaining data to obtain the preset sound intensity value.

[0038] Please continue reading Figure 2 In a preferred embodiment, the sound intensity receiving component 200 includes: at least two sound detection modules; the control module is electrically connected to the two sound detection modules respectively. The control module is configured to compare the two sets of sound intensity value information received with the corresponding preset sound intensity values. When any one of the two sets of sound intensity value information does not match the preset sound intensity value, the through hole of the core of the aviation blade is unqualified, otherwise, it is qualified. By setting two or more sets of sound detection modules and collecting the sound emitted when the airflow passes through the through hole of the core at the same time, the accuracy of the collection is improved, thereby improving the accuracy of the detection.

[0039] See also Figure 3 In at least one embodiment, the ventilation assembly 300 includes: an air pump and a ventilation box 310; the air pump is connected to the ventilation box 310; an air outlet 311 is provided on the bottom surface of the ventilation box 310; the position of the air outlet 311 is adapted to the detection slit 110, that is, the gas of the air pump enters the ventilation box 310 and is blown into the detection slit 110 through the air outlet 311. When in use, the air pump ventilates the ventilation box 310, and the airflow directly blows the detection slit 110 after passing through the air outlet 311. During detection, the through hole of the core needs to be completely aligned with the detection slit 110 before the air pump can be controlled to start supplying air.

[0040] See also Figure 3 and Figure 4In at least one embodiment, the two side walls of the air outlet 311 are respectively bonded with sealing lips 312; the two sealing lips 312 are suitable for opening the air outlet 311 when the gas is introduced into the ventilation box 310; the two sealing lips 312 are also suitable for closing the air outlet 311 when the air pump extracts the gas in the ventilation box 310, so as to detect the air tightness of the ventilation box 310. In order to allow the gas to be accurately delivered to the through hole of the core, by providing two sealing lips 312, when the gas passes through, the sealing lips 312 are opened to form an airway, guide the flow direction of the gas, and allow the airflow to enter the through hole of the core more accurately, thereby improving the accuracy of the detection. Since the detection is completely based on the sound made when the gas passes through the through hole, it is necessary to ensure that the ventilation box 310 has good sealing performance. Therefore, before each test, the air tightness of the ventilation box 310 needs to be tested. By setting two sealing lips 312, when the air pump is pumping air, the two sealing lips 312 will squeeze each other and completely close the air outlet 311. After the air outlet 311 is closed, the air pump stops pumping air. At this time, by testing whether the negative pressure in the ventilation box 310 changes significantly over a period of time, it is possible to detect whether the ventilation box 310 is leaking.

[0041] Please continue reading Figure 2 In at least one embodiment, the ventilation assembly 300 further includes a connecting frame 320 and a lifting cylinder 330; the lifting cylinder 330 is fixed on the detection base 100 through the connecting frame 320; the ventilation box 310 is fixedly arranged on the piston rod of the lifting cylinder 330, and is suitable for lifting and lowering under the drive of the lifting drive unit, so that the ventilation box 310 is close to the bottomless support tray 600, and the two sealing lips 312 are against the two sides of the through hole of the core of the aviation blade. When in use, first control the air pump to supply air to the ventilation box 310 so that the gas cleans the surface of the core, and then, by accurately controlling the extension distance of the piston rod of the lifting cylinder 330, the sealing lips 312 of the ventilation box 310 are just against the top surfaces of the two sides of the through hole of the core of the aviation blade when in the open state, thereby ensuring that the gas can be directly blown into the required area of ​​the core.

[0042] See also Figure 2 and Figure 5 In at least one embodiment, the bottom surface of the ventilation box 310 is provided with a snap ring 313 adapted to the bottomless tray 600. When the ventilation box 310 follows the piston rod of the lifting cylinder 330 to descend, the snap ring 313 is used to snap the bottomless tray 600, and the position of the bottomless tray 600 is finely adjusted, so that the through hole of the core in the bottomless tray 600 can be accurately aligned with the detection slit 110.

[0043] It should be noted that the core is clamped on the bottomless tray 600 . When the bottomless tray 600 is clamped with the clamping ring 313 on the bottom surface of the ventilation box 310 , the through hole of the core is exactly opposite to the air outlet 311 of the ventilation box 310 .

[0044] See also Figure 2 and Figure 6 Since the core has two rows of through holes, in order to detect the two rows of through holes respectively, in at least one embodiment, the snap ring 313 is slidably disposed on the bottom surface of the ventilation box 310. During the detection, the material moving assembly 500 makes the through holes in the first row of the bottomless tray 600 face the detection slit 110 to complete the detection of the first row of through holes, and then moves the bottomless tray 600 to make the through holes in the second row face the detection slit 110 to complete the detection of the second row of through holes.

[0045] Please continue reading Figure 1 , at least one embodiment has also passed an automated testing production line, including: a control module, a testing base 100, a sound intensity receiving component 200, a ventilation component 300, a discharging component 700, a material transfer component 500 and a bottomless tray 600; the testing base 100 is arranged on the feeding side of the discharging component 700; the sound intensity receiving component 200 is arranged on the testing base 100; the ventilation component 300 is arranged above the testing base 100; a testing slit 110 is arranged on the testing base 100; the bottomless tray 600 carries the core of the aviation blade to be tested; the sound intensity receiving component 200 is suitable for receiving the sound intensity value information when the gas blows through the through hole of the core of the aviation blade, and sending the sound intensity value information to the control module; the control module is suitable for detecting the through hole of the core of the aviation blade according to the sound intensity value information, and controlling the material transfer component 500 to transport the core of the aviation blade that has been tested to the corresponding conveying area of ​​the discharging component 700 according to the detection result.

[0046] Specifically, the discharge assembly 700 includes a first discharge channel 710 and a second discharge channel 720, and a switching plate 730 is arranged between the first discharge channel 710 and the second discharge channel 720, and the switching plate 730 is controlled by a steering gear. When it is detected that the core of the aviation blade is unqualified, the control module controls the steering gear to rotate, thereby driving the switching plate 730 to rotate, opening the second discharge channel 720 and closing the first discharge channel 710; when it is detected that the new type of aviation blade is qualified, the control module controls the steering gear to rotate, thereby driving the switching plate 730 to rotate, closing the second discharge channel 720 and opening the first discharge channel 710.

[0047] In at least one embodiment, a method for detecting a core of an aircraft blade is provided, wherein the method is suitable for detecting the core of an aircraft blade conveyed by the above-mentioned automated detection production line.

[0048] Specifically, the method includes: controlling the material transfer component 500 to move the bottomless support tray 600 to the detection base 100; controlling the ventilation component 300 to ventilate the through holes of the core of the aviation blade on the seamless tray; receiving the sound intensity value information when the gas blows through the through holes of the core of the aviation blade through the sound intensity receiving component 200; and completing the detection of the through holes of the core of the aviation blade based on the sound intensity value information.

[0049] Based on the above ideal embodiments of the present invention, the relevant staff can make various changes and modifications without departing from the technical concept of the present invention through the above description. The technical scope of the present invention is not limited to the contents of the specification, and its technical scope must be determined according to the scope of the claims.

Claims

1. An automated testing production line, characterized in that: include: Control module, detection base, sound intensity receiving component, ventilation component, feeding component, material moving component and bottomless tray; The detection base is arranged on the discharge side of the feeding assembly; The sound intensity receiving component is arranged on the detection base; The ventilation assembly is arranged above the detection base; The detection base is provided with a detection slit; The bottomless tray carries a core of an aviation blade to be inspected; The material transfer assembly is adapted to move the bottomless tray conveyed by the material feeding assembly to the detection base, and to move the through hole of the core of the aviation blade in the bottomless tray to between the ventilation assembly and the detection slit; The sound intensity receiving component is adapted to receive sound intensity value information when gas blows through the through hole of the core of the aviation blade, and send the sound intensity value information to the control module; The control module is suitable for detecting the through hole of the core of the aviation blade according to the sound intensity value information.

2. The automated testing production line according to claim 1, characterized in that: The control module stores preset sound intensity values ​​of the through holes of the core of a qualified aviation blade after ventilation; The control module is configured to compare the received sound intensity value information with a preset sound intensity value, thereby completing the detection of the through hole of the core of the aviation blade.

3. The automated testing production line according to claim 2, characterized in that: The sound intensity receiving component includes: at least two sound detection modules; The control module is electrically connected to the two sound detection modules respectively.

4. The automated testing production line according to claim 3, characterized in that: The control module is configured to compare the two sets of received sound intensity value information with the corresponding preset sound intensity values ​​respectively. When any one of the two sets of sound intensity value information does not match the preset sound intensity value, the through hole of the core of the aviation blade is unqualified, otherwise, it is qualified.

5. The automated testing production line according to claim 1, characterized in that: The ventilation assembly includes: an air pump and a ventilation box; The air pump is in communication with the ventilation box; The bottom surface of the ventilation box is provided with an air outlet; The position of the air outlet is adapted to the detection slit, that is, the gas from the air pump enters the ventilation box and is blown into the detection slit through the air outlet.

6. The automated testing production line according to claim 5, characterized in that: The two side walls of the air outlet are respectively bonded with sealing lips; The two sealing lips are suitable for opening the air outlet when gas is introduced into the ventilation box; The two sealing lips are also suitable for closing the air outlet when the air pump extracts the gas in the ventilation box, so as to detect the air tightness of the ventilation box.

7. The automated testing production line according to claim 6, characterized in that: The ventilation assembly also includes a connecting frame and a lifting cylinder; The lifting cylinder is fixed on the detection base through a connecting frame; The ventilation box is fixedly arranged on the piston rod of the lifting cylinder and is suitable for lifting and lowering under the drive of the lifting drive unit, so that the ventilation box is close to the bottomless support tray and the two sealing lips are abutted against both sides of the through hole of the core of the aviation blade.

8. The automated testing production line according to claim 7, characterized in that: The bottom surface of the ventilation box is provided with a snap ring matched with the bottomless support tray.

9. The automated testing production line according to claim 8, characterized in that: The clamping ring is slidably arranged on the bottom surface of the ventilation box.

10. An automated testing production line, characterized in that: include: Control module, detection base, sound intensity receiving component, ventilation component, discharging component, material transfer component and bottomless tray; The detection base is arranged on the feeding side of the discharging assembly; The sound intensity receiving component is arranged on the detection base; The ventilation assembly is arranged above the detection base; The detection base is provided with a detection slit; The bottomless tray carries a core of an aviation blade to be inspected; The sound intensity receiving component is adapted to receive sound intensity value information when gas blows through the through hole of the core of the aviation blade, and send the sound intensity value information to the control module; The control module is suitable for detecting the through holes of the core of the aircraft blade according to the sound intensity value information, and controlling the material transfer component to transport the inspected core of the aircraft blade to the corresponding conveying area of ​​the discharging component according to the detection result.

11. A core detection method for an aviation blade, characterized in that: The method is suitable for testing the core of an aviation blade conveyed by the automated testing production line provided by any one of claims 1 or 10, and the method comprises: Control the material transfer assembly to move the bottomless tray onto the detection base; Controlling the ventilation assembly to ventilate the through holes of the core of the aviation blade on the seamless tray; The sound intensity value information when the gas blows through the through hole of the core of the aviation blade is received by the sound intensity receiving component; The detection of the through hole of the core of the aviation blade is completed based on the sound intensity value information.

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