Desoldering detection device for aerospace component processing

Abstract

This invention discloses a desoldering detection device for aerospace component processing, belonging to the field of welding inspection technology. It includes a test bench and a simulation ring for inspecting turbine blade components. The turbine blade components consist of assembly tenons and hollow blades. A high-pressure blower is fixed to the top of the test bench via a mounting base, and the high-pressure blower is connected to a fixing ring via a pressure cylinder. Through the setting of the pressurization component, this invention utilizes a ring-shaped reverse pressure system composed of Z-shaped holes on the ring-shaped reverse pressure seat and a pressurization impeller to achieve a high-temperature, high-pressure simulated airflow reversal environment from relatively low pressure to high pressure, simulating real aerodynamic conditions between turbine stages. Simultaneously, the setting of fluorescent liquid in the storage tank allows for the use of fluorescent airflow visualization technology and the microporous seepage characteristics of abnormal fluorescent liquid seepage at the sealing defect location. A high-speed industrial camera records abrupt changes in the streamlines on the surface of the hollow blade, achieving surface flow field distortion capture and rapid, accurate location of desoldering and crack defects.

Description

Technical Field

[0001] This invention relates to the field of welding inspection technology, and in particular to a desoldering inspection device for aerospace component processing. Background Technology

[0002] Turbine blades are an important component of aero engines. During the casting process, process holes need to be reserved inside the blade to fill the core or discharge casting sand. After molding, these process holes need to be permanently sealed with precision welding to prevent hot airflow from entering and to ensure the integrity of the blade's external aerodynamic profile and avoid stress concentration.

[0003] Currently, after precision welding of the process holes in aerospace turbine blades and subsequent non-destructive testing such as ultrasonic testing, the turbine blades are assembled with the turbine disk and then subjected to subsequent operational testing. However, some turbine blades show no obvious welding quality problems after welding, but when subjected to high-temperature and high-pressure airflow, weld detachment occurs. If such problems are not detected in time, they may occur during subsequent operational testing after assembly, and the detached welding material may damage the high-speed rotating turbine blades, causing significant economic losses. Furthermore, aerospace turbine blades achieve an unconventional flow state from low pressure to high pressure through the special cooperation between the moving and stationary blades. However, it is difficult to reproduce such special working conditions when testing individual aerospace turbine blades, resulting in inaccurate test data. Therefore, a weld detachment detection device for aerospace component processing is proposed. Summary of the Invention

[0004] The purpose of this invention is to solve the problems in the prior art by proposing a desoldering detection device for the processing of aerospace components.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A desoldering detection device for aerospace component processing includes a test bench and a simulation ring for detecting turbine blade components. The turbine blade components consist of assembly tenons and hollow blades. A high-pressure blower is fixed to the top of the test bench via a mounting base. The high-pressure blower is connected to a fixing ring via a pressure cylinder. A marking assembly is provided on the pressure cylinder. The fixing ring is connected to a test seat via a fixing mesh plate. Multiple sets of flow guiding assemblies are provided on the test seat.

[0007] The simulation ring is connected to multiple one-way valves via an equal pressure ring. A wind pressure simulation component is installed outside the one-way valves. An annular reverse pressure seat is connected to the inner wall of the simulation ring. Multiple Z-shaped reverse pressure holes are opened on the annular reverse pressure seat. A pressure accumulator impeller is installed in the vertical diameter of the Z-shaped reverse pressure hole. A pressurizing component for simulating the reverse pressure condition of turbine blade components is installed on one side of the pressure accumulator impeller.

[0008] Preferably, the top of the test bench is fixedly connected to the outer wall of the simulation ring via a support, the output end of the high-pressure blower is connected to the fixed ring via a pressure cylinder, and the fixed ring is connected to the booster tail nozzle via the simulation ring.

[0009] Preferably, the marking assembly includes a storage box fixed to the top of the air pressure cylinder, the storage box being connected to the inside of the air pressure cylinder via an atomizing nozzle, and the storage box containing fluorescent liquid.

[0010] Preferably, the retaining mesh plate is rotatably connected to the test seat via a fixed shaft, and the retaining mesh plate is fixedly connected to a simulated stationary blade via the fixed shaft. The test seat has multiple assembly slots that are adapted to the assembly tenons, and the multiple assembly slots are arranged in a ring array.

[0011] Preferably, the flow guiding assembly includes two retaining rods disposed on both sides of the hollow blade, a plurality of linear flow guide plates are installed on the outer wall of the retaining rods, and a high-speed industrial camera is fixedly connected to the end of the retaining rod.

[0012] Preferably, the wind pressure simulation component includes multiple isobaric air pumps fixed on the outer wall of the simulation ring, the isobaric air pumps being interconnected with an isobaric heating ring, and the isobaric heating ring being disposed on the outer wall of the isobaric ring.

[0013] Preferably, one end of the Z-shaped reverse pressure hole is located on one side of the isobaric heating ring, the inner wall of the simulated ring is fixedly connected to the annular reverse pressure seat, and the simulated ring is fixedly connected to the pressure accumulating impeller through multiple shafts.

[0014] Preferably, the booster assembly includes a booster impeller, which is disposed on the other side of the Z-shaped reverse pressure hole. A drive motor is fixedly connected to the side wall of the annular reverse pressure seat via a right-angle plate, and the output end of the drive motor is fixedly connected to the booster impeller via a rotating shaft.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0016] 1. This solution, through the setting of the flow guide component, can use the deflection of the linear flow guide plate to adjust the local pressure distribution of the leading edge, back, blade base and trailing edge of the hollow blade, accurately reproduce the air pressure changes in the early stage of startup, steady-state operation and the final stage of load reduction, realize dynamic load simulation, and make the test data richer.

[0017] 2. By setting up the pressurization component, this solution can utilize the annular reverse pressure system composed of the Z-shaped hole on the annular reverse pressure seat and the pressurization impeller to realize the high temperature and high pressure simulated airflow reverse flow environment from relatively low pressure to high pressure, simulate the real aerodynamic conditions between turbine stages, and make the test of the turbine blade mechanism more closely match the real operating conditions.

[0018] 3. This solution utilizes fluorescent liquid in the storage tank to visualize fluorescent airflow and the microporous seepage characteristics of abnormal fluorescent liquid seepage at the sealing defect. A high-speed industrial camera is used to record abrupt changes in the streamlines on the surface of the hollow blade, thereby capturing surface flow field distortion and quickly and accurately locating weld debonding and crack defects. Attached Figure Description

[0019] Figure 1 This is a three-dimensional structural schematic diagram of the desoldering detection device for aerospace component processing proposed in this invention;

[0020] Figure 2 This is an overall assembly drawing of the desoldering detection device for aerospace component processing proposed in this invention;

[0021] Figure 3 for Figure 2 Enlarged view of point A in the middle;

[0022] Figure 4 This is a schematic diagram of the test stand in the desoldering detection device for aerospace parts processing proposed in this invention;

[0023] Figure 5 This is an assembly drawing of the turbine blade component and test base in the desoldering detection device for aerospace parts processing proposed in this invention;

[0024] Figure 6 This is a schematic diagram of the annular reverse pressure seat in the desoldering detection device for aerospace parts processing proposed in this invention;

[0025] Figure 7 This is an assembly diagram of the simulated ring in the desoldering detection device for aerospace component processing proposed in this invention;

[0026] Figure 8 for Figure 7 Enlarged view of point B in the middle;

[0027] Figure 9 This is a partial cross-sectional view of the simulated ring in the desoldering detection device for aerospace component processing proposed in this invention;

[0028] Figure 10 This is a test flowchart of the desoldering detection device for aerospace component processing proposed in this invention.

[0029] In the diagram: 1. Test bench; 2. Simulation ring; 3. Assembly tenon; 4. Hollow blade; 5. High-pressure blower; 6. Storage tank; 7. Fixing ring; 8. Fixing mesh plate; 9. Test seat; 10. Simulated stationary blade; 11. Fixing rod; 12. Linear guide plate; 13. High-speed industrial camera; 14. Isobaric air pump; 15. Isobaric heating ring; 16. Isobaric ring; 17. One-way valve; 18. Annular reverse pressure seat; 19. Accumulator impeller; 20. Drive motor; 21. Booster impeller; 22. Booster tail spray. Detailed Implementation

[0030] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0031] In the description of this invention, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0032] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0033] Example, refer to Figures 1 to 10 A desoldering detection device for aerospace parts processing includes a test bench 1 and a simulation ring 2 for detecting turbine blade components. The turbine blade components are composed of assembly tenons 3 and hollow blades 4. A high-pressure blower 5 is fixed to the top of the test bench 1 by a mounting base. The high-pressure blower 5 is connected to a fixing ring 7 through a pressure cylinder. A marking component is set on the pressure cylinder. The fixing ring 7 is connected to a test seat 9 through a fixing mesh plate 8. Multiple sets of flow guiding components are set on the test seat 9.

[0034] Furthermore, the top of the test stand 1 is fixedly connected to the outer wall of the simulation ring 2 via a support, the output end of the high-pressure blower 5 is connected to the fixed ring 7 via the air pressure cylinder, the fixed ring 7 is connected to the booster tail spray 22 via the simulation ring 2, the marking component includes a storage box 6 fixed to the top of the air pressure cylinder, the storage box 6 is connected to the inside of the air pressure cylinder via an atomizing nozzle, the storage box 6 is filled with fluorescent liquid, the fixed mesh plate 8 is rotatably connected to the test seat 9 via a fixed shaft, the fixed mesh plate 8 is fixedly connected to the simulation stationary blade 10 via a fixed shaft, the test seat 9 is provided with multiple assembly slots that are compatible with the assembly tenon 3, the multiple assembly slots are arranged in a ring array, the flow guiding component includes two fixed rods 11 set on both sides of the hollow blade 4, multiple linear flow guiding plates 12 are installed on the outer wall of the fixed rods 11, and a high-speed industrial camera 13 is fixedly connected to the end of the fixed rods 11;

[0035] It should be noted that: the detachable turbocharger nozzle 22 is removed from the simulation ring 2, and then the assembly tenon 3 of the turbine blade component to be tested is assembled into the assembly slot on the test seat 9. Then the turbocharger nozzle 22 is reassembled, and then the high-pressure blower 5 is started to output high-pressure airflow to blow the assembled hollow blades 4. During this process, the fluorescent liquid in the storage tank 6 is sprayed out through the atomizer nozzle and mixed with fluorescent water mist to enter the high-pressure airflow, blowing the hollow blades 4. The hollow blades 4 rotate on the fixed shaft due to the airflow change, while the wheel of the simulated stationary blade 10 remains stationary. This is used to simulate the front and rear airflow change state of the alternating front and rear set of the moving and stationary blades in the turbine blade, which is more accurate than the individual test of the hollow blades 4.

[0036] During the test, the fluorescent airflow changes on the surface of the hollow blade 4, and some fluorescent fluid passes through the micropores on the surface of the hollow blade 4. The overall flow change of the airflow on the surface of the hollow blade 4 is regular. The high-speed industrial camera 13 records the entire process. If defects such as detachment occur at the sealing weld of the turbine blade mechanism, the flow integrity of the entire surface of the hollow blade 4 will be destroyed, thereby changing the flow change of the fluorescent fluid on the hollow blade 4. This defect can be captured and recorded by the high-speed industrial camera 13. At the same time, under the influence of the linear guide plate 12 at the stationary rod 11, the local airflow will change direction and pressurize. If the linear guide plate 12 guides and pressurizes the surrounding airflow to the surface of the hollow blade 4, it will make the area of ​​the hollow blade 4 with higher pressure than other areas. If the linear guide plate 12 guides the airflow on the hollow blade 4 to the surrounding area, it will make the area with relatively low pressure. These are adjusted by the installation deflection direction of the linear guide plate 12 on the stationary rod 11.

[0037] The advantages mentioned above are as follows: under the condition that the hollow blade 4 is affected by the high-pressure airflow as a whole, the leading edge, back, base and trailing edge of the hollow blade 4 are subjected to more differentiated pressure load changes, which can be used to simulate the different load changes in each area of ​​the hollow blade 4 in the early stage of startup, the stable operation stage and the end of operation, making the test more accurate and the test data richer.

[0038] The simulation ring 2 is connected to multiple one-way valves 17 via an equal pressure ring 16. A wind pressure simulation component is installed outside the one-way valves 17. An annular reverse pressure seat 18 is connected to the inner wall of the simulation ring 2. Multiple Z-shaped reverse pressure holes are opened on the annular reverse pressure seat 18. A pressure accumulator impeller 19 is installed in the vertical diameter of the Z-shaped reverse pressure hole. A pressurizing component for simulating the reverse pressure condition of turbine blade components is installed on one side of the pressure accumulator impeller 19.

[0039] Furthermore, the wind pressure simulation component includes multiple isobaric air pumps 14 fixed on the outer wall of the simulation ring 2. The isobaric air pumps 14 are interconnected with the isobaric heating ring 15. The isobaric heating ring 15 is disposed on the outer wall of the isobaric ring 16. One end of the Z-shaped reverse pressure hole is disposed on one side of the isobaric heating ring 15. The inner wall of the simulation ring 2 is fixedly connected to the annular reverse pressure seat 18. The simulation ring 2 is fixedly connected to the pressure accumulator impeller 19 through multiple shafts. The pressurization component includes a pressurization impeller 21, which is disposed on the other side of the Z-shaped reverse pressure hole. The side wall of the annular reverse pressure seat 18 is fixedly connected to a drive motor 20 through a right-angle plate. The output end of the drive motor 20 is fixedly connected to the pressurization impeller 21 through a rotating shaft.

[0040] It should be noted that during the entire simulation test, multiple isobaric air pumps 14 on simulation ring 2 are simultaneously activated, and the gradually increasing airflow is heated in isobaric heating ring 15 to facilitate the subsequent simulation of the high-temperature and high-pressure airflow conditions. After the air pressure in isobaric heating ring 15 reaches the target, multiple one-way valves 17 on isobaric ring 16 are simultaneously opened, allowing the high-temperature and high-pressure airflow to enter simulation ring 2 in a ring-shaped manner. Subsequently, the high-temperature and high-pressure airflow enters the Z-shaped hole of the annular reverse pressure seat 18, where the high-temperature and high-pressure airflow will be temporarily sealed within the pressure-accumulating fixed blade in the Z-shaped hole. In the cavity of wheel 19, the drive motor 20 will continuously drive the booster impeller 21 to rotate, so that the booster impeller 21 draws in the high temperature and high pressure airflow in the Z-shaped hole and forms a higher pressure airflow state at the booster impeller 21. Then, relative to the annular reverse pressure seat 18, there is a reverse flow from a relatively low pressure airflow environment to a higher pressure airflow environment, so as to simulate the actual working condition of the hollow blade 4 between the annular reverse pressure seat 18. The booster tail nozzle 22 can keep the air pressure in a continuous booster flow state and avoid the backflow of airflow from affecting the test in the simulation ring 2.

[0041] The advantages mentioned above are: this allows for the simulation of a reverse flow state from a low-pressure airflow environment to a high-pressure airflow environment during the testing of hollow blade 4, which facilitates the simulation of the actual operating conditions of the turbine blade mechanism, making the entire test more accurate and reliable.

[0042] In use, the detachable turbocharger nozzle 22 is removed from the simulation ring 2. Then, the assembly tenon 3 of the turbine blade component to be tested is assembled into the assembly slot on the test seat 9. The turbocharger nozzle 22 is then reassembled. The high-pressure blower 5 is then started to output high-pressure airflow to blow the assembled hollow blades 4. During this process, the fluorescent liquid in the storage tank 6 is sprayed out through the atomizer nozzle and mixed with fluorescent water mist to enter the high-pressure airflow, blowing the hollow blades 4. The hollow blades 4 rotate on the fixed shaft due to the airflow change, while the wheel of the simulated stationary blade 10 remains stationary. This is used to simulate the front and rear airflow change state of the alternating front and rear arrangement of the moving and stationary blades in the turbine blade, which is more accurate than the individual test of the hollow blades 4.

[0043] During the test, the fluorescent airflow changes on the surface of the hollow blade 4, and some fluorescent fluid passes through the micropores on the surface of the hollow blade 4. The overall flow change of the airflow on the surface of the hollow blade 4 is regular. The high-speed industrial camera 13 records the entire process. If defects such as weld failure occur at the sealing weld of the turbine blade mechanism, the flow integrity of the entire surface of the hollow blade 4 will be destroyed, thereby changing the flow change of the fluorescent fluid on the hollow blade 4. This defect can be captured and recorded by the high-speed industrial camera 13. At the same time, under the influence of the linear guide plate 12 at the stationary rod 11, the airflow will locally change direction and pressurize at the linear guide plate 12. If the linear guide plate 12 guides and pressurizes the surrounding airflow to the surface of the hollow blade 4, it will make the area of ​​the hollow blade 4 intersecting with other areas of higher pressure. If the linear guide plate 12 guides the airflow on the hollow blade 4 to the surrounding area, it will make the area of ​​the hollow blade 4 relatively low pressure. These are adjusted by the installation deflection direction of the linear guide plate 12 on the fixing rod 11. In this way, under the condition that the hollow blade 4 is affected by the high pressure airflow as a whole, the leading edge, blade back, blade base and trailing edge of the hollow blade 4 will be subjected to greater differentiated pressure load changes. This can be used to simulate the different load changes in each area of ​​the hollow blade 4 in the early stage of startup, the stable operation stage and the end of operation, so that the test is more accurate and the test data is richer.

[0044] During the entire simulation test, multiple isobaric air pumps 14 on simulation ring 2 are simultaneously activated, and the gradually increasing airflow is heated in isobaric heating ring 15 to facilitate the subsequent simulation of the high-temperature and high-pressure airflow conditions. After the air pressure in isobaric heating ring 15 reaches the target, multiple one-way valves 17 on isobaric ring 16 are simultaneously opened, allowing the high-temperature and high-pressure airflow to enter simulation ring 2 in a ring-shaped instantaneous manner. Subsequently, the high-temperature and high-pressure airflow enters the Z-shaped hole of the annular reverse pressure seat 18, where it is temporarily sealed in the cavity of the pressure-accumulating impeller 19 within the Z-shaped hole. At this time, the drive motor 20 continuously drives the booster impeller 21 to rotate, causing the booster impeller 21 to pressurize the airflow within the Z-shaped hole. High-temperature, high-pressure airflow is drawn in, forming an even higher-pressure airflow state at the booster impeller 21. This creates a reverse flow from a relatively low-pressure airflow environment to a higher-pressure airflow environment relative to the annular reverse pressure seat 18. This facilitates the simulation of the actual working conditions of the hollow blades 4 between the annular reverse pressure seat 18. The booster nozzle 22 keeps the air pressure in a continuous booster flow state, preventing the reverse flow from affecting the test in the simulation ring 2. In this way, during the test of the hollow blades 4, a reverse flow state from a low-pressure airflow environment to a high-pressure airflow environment can be simulated, which is convenient for simulating the actual working conditions of the turbine blade mechanism during operation, making the entire test more accurate and reliable.

[0045] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A de-bonding detection device for aerospace parts machining, comprising a test bench (1) and a simulation ring (2) for detecting a turbine blade component, said turbine blade component consisting of an assembly tenon (3) and a hollow blade (4), characterized in that, The test bench (1) top is fixed with high pressure fan (5) through mounting seat, high pressure fan (5) is connected with fixed ring (7) through wind pressure cylinder, wind pressure cylinder is provided with mark assembly, fixed ring (7) is connected with test seat (9) through retaining web plate (8), test seat (9) is provided with multiple groups of flow guide assembly; The simulation ring (2) is connected with multiple one-way valves (17) through the equal pressure ring (16), the one-way valves (17) are provided with a wind pressure simulation assembly outside, the simulation ring (2) is connected with a ring-shaped counter-pressure seat (18) on the inner side wall, a plurality of Z-shaped counter-pressure holes are formed in the ring-shaped counter-pressure seat (18), a pressure storage fixed impeller (19) is arranged in the vertical aperture of the Z-shaped counter-pressure hole, a pressure boosting assembly for simulating the counter-pressure working condition of the turbine blade component is arranged on one side of the pressure storage fixed impeller (19). The flow guide assembly includes two retaining rods (11) arranged on both sides of the hollow blade (4), a plurality of linear flow guide plates (12) are mounted on the outer wall of the retaining rod (11), a high-speed industrial camera (13) is fixedly connected to the end of the retaining rod (11), the wind pressure simulation assembly includes a plurality of equal pressure air pumps (14) fixed on the outer side wall of the simulation ring (2), the equal pressure air pumps (14) and the equal pressure heating ring (15) are in communication with each other, the equal pressure heating ring (15) is arranged on the outer side wall of the equal pressure ring (16), the pressure boosting assembly includes a pressure boosting impeller (21), the pressure boosting impeller (21) is arranged on the other side of the Z-shaped counter-pressure hole, the side wall of the ring-shaped counter-pressure seat (18) is fixedly connected with a drive motor (20) through a right-angle plate, the output end of the drive motor (20) is fixedly connected with the pressure boosting impeller (21) through a rotating shaft.

2. The de-bonding detection device for aerospace parts machining as claimed in claim 1, wherein, The test bench (1) top is fixedly connected with the simulation ring (2) through the support and the outer side wall of the simulation ring (2), the output end of the high pressure fan (5) is communicated with the fixed ring (7) through the wind pressure cylinder, the fixed ring (7) is communicated with the pressure boosting tail jet (22) through the simulation ring (2).

3. The de-bonding detection device for aerospace parts machining as claimed in claim 1, wherein, The mark assembly includes a storage box (6) fixed on the top of the wind pressure cylinder, the storage box (6) is communicated with the inside of the wind pressure cylinder through an atomizing nozzle, and the storage box (6) contains fluorescent liquid.

4. The de-bonding detection device for aerospace parts machining of claim 1, wherein, The retaining web plate (8) is rotatably connected with the test seat (9) through a fixing shaft, the retaining web plate (8) is fixedly connected with a simulation stationary blade (10) through a fixing shaft, a plurality of assembly grooves compatible with the assembly tenon (3) are formed in the test seat (9), and the plurality of assembly grooves are arranged in an annular array.

5. The de-bonding detection device for aerospace parts machining of claim 1, wherein, One end of the Z-shaped counter-pressure hole is arranged on one side of the equal pressure heating ring (15), the inner wall of the simulation ring (2) is fixedly connected with the ring-shaped counter-pressure seat (18), and the simulation ring (2) is fixedly connected with the pressure storage fixed impeller (19) through multiple shaft rods.

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