Worm wheel blade surface film hole optimization structure and detection tool and detection method thereof

Abstract

The invention relates to a worm wheel blade surface film hole optimization structure and a detection tool and method thereof. The structure comprises a fixing seat and a blade body, an air inlet is formed in one side of the fixing seat, and a connecting tenon is arranged at the bottom of the fixing seat; one side of the blade main body is a concave pressure-bearing side surface, the other side of the blade main body is a convex back-pressure side surface, and a plurality of groups of air film holes are formed in the pressure-bearing side surface and face the tail edge of the blade main body; a cavity is formed in the blade main body, a plurality of supporting rib plates are arranged in the cavity to divide the cavity into a plurality of flow passing channels, each group of air film holes are correspondingly communicated with the flow passing channels, and each flow passing channel is communicated with the air inlet hole; blade top partition plates are fixedly arranged at the tops of the supporting rib plates. The detection tool comprises a turbine disc, a front fixing ring, a front baffle ring, a rear fixing ring, a rear baffle ring, a mounting shaft and the like, colored smoke is input into a main gas channel in the mounting shaft, the flowing state of gas on the surface of a blade is observed, and quality classification is conducted on products. The blade cooling efficiency is improved, and the service life is prolonged.

Description

Technical Field

[0001] This invention relates to the field of turbomachinery, specifically to an optimized structure for film pores on the surface of a worm gear blade, and its testing fixture and method. Background Technology

[0002] With the continuous development of aero-engine and gas turbine technologies, turbine blades, as one of their core components, are facing increasingly higher operating temperatures, placing greater demands on blade cooling technology. Film cooling, as a crucial method for turbine blade cooling, has a significant impact on blade lifespan and overall turbine performance due to its structural design and layout.

[0003] Currently, turbine blade film cooling technology mainly achieves this by creating film cooling holes on the blade surface to introduce cooling gas and form a protective film. CN107143383B discloses a film cooling hole layout structure for the pressure surface and top composite angle of a turbine blade. This structure divides the turbine blade pressure surface from the blade root to the blade tip into multiple regions and sets film cooling holes with different composite angles in different regions to overcome the problem of deflection of the pressure surface film outflow under the influence of various forces. CN112780357A proposes a film cooling hole structure based on the vortex effect. Through a specially designed vortex chamber, a lower-temperature cold gas flow is separated to provide lower-temperature cooling gas for walls with high cooling performance requirements.

[0004] Regarding film cooling in the trailing edge region of turbine blades, CN116220829B discloses a method for suppressing local film cooling failure at the trailing edge of turbine blades. This method divides the trailing half of the blade root into a film cooling failure triangle zone and adds non-uniformly arrayed film cooling holes within the zone. The film cooling holes adopt a funnel-shaped tapering hole structure to improve the cooling effect in the trailing edge region. CN115434757A proposes a combined film cooling hole and turbine blade. This structure includes dual-row film cooling holes, which effectively suppress the harmful characteristic of cylindrical holes being easily blown away under high airflow ratios through a specific arrangement.

[0005] However, existing turbine blade film cooling structures still have the following technical problems: 1. Uneven and easily peeled-off air film coverage: The existing air film hole arrangement and injection angle design are not reasonable enough, making it difficult for the cooling gas to form a uniform and stable air film coverage on the blade surface. Especially on the pressure-bearing side of the blade, the air film is easily peeled off by the mainstream gas, resulting in insufficient cooling in local high-temperature areas, which in turn leads to problems such as ablation and cracking of the blade material.

[0006] 2. Insufficient internal support structure of the blades: Most existing turbine blades adopt a hollow structure to reduce weight and provide cooling gas channels, but they lack an effective internal support structure, resulting in insufficient overall blade stiffness. Under high-speed rotation conditions, they are prone to deformation or even breakage. Although CN114810216A proposes a scheme to install baffles inside the blades, the coordinated design of its baffle structure and film cooling holes still needs to be optimized.

[0007] 3. Low efficiency of cooling gas utilization: In existing blade structures, the cooling gas suffers from uneven distribution and local short-circuiting when flowing inside the blade, resulting in insufficient or excessive gas supply to some film cooling pores, affecting the overall cooling effect. Especially in the blade tip region, due to the lack of an effective sealing structure, a large amount of cooling gas leaks directly from the blade tip and fails to effectively participate in the film cooling process.

[0008] 4. Lack of effective testing methods: Existing testing methods and tooling equipment for turbine blade film cooling holes are difficult to accurately simulate the actual working state of the blades, and cannot intuitively and comprehensively evaluate the flow performance and cooling effect of the film cooling holes, resulting in great difficulty in blade quality control and potential safety hazards.

[0009] Therefore, there is an urgent need to develop a new type of optimized structure for the air film pores on the surface of worm gear blades and its testing fixture, in order to solve the above-mentioned technical problems and improve the cooling efficiency and service life of turbine blades. Summary of the Invention

[0010] To address the technical problems of existing turbine blade film pore structures, such as uneven and easily peeled film coverage, insufficient structural strength of hollow blades, serious cooling gas leakage, and outdated testing tools and methods, and to achieve significant improvements in cooling effect, enhanced structural strength and reliability, maximized cooling gas utilization, accurate, intuitive and efficient testing, and strong structural adaptability and practicality, this invention provides an optimized turbine blade film pore structure and matching testing tools.

[0011] The technical solution adopted by this invention to solve its technical problem is: an optimized structure for film gas pores on the surface of a worm gear blade, including a fixed base, an air inlet hole provided on one side of the fixed base, a connecting tenon provided at the bottom of the fixed base, and a blade body provided at the top of the fixed base. One side wall of the blade body is a concave pressure-bearing side, and the other opposite side wall is a convex back pressure side. Several sets of film gas pores are provided on the pressure-bearing side, and each film gas pore on the pressure-bearing side faces the trailing edge of the blade body. A cavity is provided inside the blade body, and several supporting ribs are provided in the cavity of the blade body. The several supporting ribs divide the cavity inside the blade body into several flow channels. Each set of film gas pores is respectively connected to several flow channels, and each flow channel is connected to the air inlet hole. A blade tip baffle is fixedly provided on the top of the several supporting ribs, and the blade tip baffle is connected to the inner cavity side wall of the blade body.

[0012] Preferably, air film pores are also provided at the leading edge of the blade tip septum and the blade body.

[0013] Preferably, the inspection fixture for detecting the optimized structure of the film cooling hole on the surface of a worm gear blade includes a turbine disk. A shaft hole is formed in the center of the turbine disk, and an air inlet groove is formed on the inner wall of the shaft hole. Several connecting riveting grooves are evenly formed on the side wall of the turbine disk, and these grooves match the connecting tenons. A front fixing ring is provided on one end face of the turbine disk, and a front retaining ring is detachably mounted on the front fixing ring. A rear fixing ring is provided on the other end face of the turbine disk, and a connecting groove is formed on the rear fixing ring. The connecting groove communicates with the air inlet groove through several guide holes formed inside the turbine disk. A rear retaining ring is detachably mounted on the rear fixing ring, and a connecting hole is also provided on one end face of the rear retaining ring. The other end of the connecting hole is located on the inner wall of the rear retaining ring. When the blade body is connected to the turbine disk, the connecting tenon is located between the front retaining ring and the rear retaining ring. One end of the connecting hole on the rear retaining ring is connected to the air inlet, and the other end is connected to the connecting groove.

[0014] Furthermore, the testing fixture also includes a mounting shaft with a limiting protrusion fixedly provided on it. A main air passage is formed on one end face of the mounting shaft, and a bypass air passage is formed on the mounting shaft on one side of the limiting protrusion. The bypass air passage is connected to the main air passage. When the turbine disk is detachably connected to the mounting shaft through the shaft hole, and when the turbine disk is fitted onto the mounting shaft and fits against the limiting protrusion, the bypass air passage is connected to the air inlet groove.

[0015] Optionally, a plurality of front fixing holes are provided on the front fixing ring, and the same number of front mounting holes are provided on the front retaining ring. After the front retaining ring is fitted onto the front fixing ring, the front retaining ring and the front fixing ring are fixedly connected by passing a bolt through the front mounting hole and screwing it into the front fixing hole. Similarly, a plurality of rear fixing holes are provided on the rear fixing ring, and the same number of rear mounting holes are provided on the rear retaining ring. After the rear retaining ring is fitted onto the front fixing ring, the rear retaining ring and the rear fixing ring are fixedly connected by passing a bolt through the rear mounting hole and screwing it into the rear fixing hole.

[0016] Preferably, sealing elements are provided at both ends of the air inlet groove and the connecting groove.

[0017] Furthermore, the method for using a detection fixture based on the optimized structure of the film pores on the surface of the worm gear blade includes the following steps: S1, Install the front retaining ring onto the front retaining ring and secure it; S2, install the blade body onto the turbine disk, and make the end of the blade body's mounting base without an air intake hole fit against the front baffle ring; S3, install the rear retaining ring onto the rear retaining ring and secure it. After the rear retaining ring and the rear retaining ring are fitted together, the connecting hole will connect the connecting groove with the air intake. Then connect the turbine disc to the mounting shaft. S4. Introduce colored smoke into the main air duct on the mounting shaft and let it flow out from the air film holes on the blade body. Observe the flow state of the gas flowing out from the air film holes on the surface of the blade body. Classify the finished product and the defective product according to the flow state of the colored gas on the surface of the blade body.

[0018] Compared with the prior art, the present invention has the following advantages: 1. Significantly improved cooling effect: By designing the air film vents on the pressure-bearing side to face the trailing edge, the cooling gas is spread along the blade surface in a downstream direction. Combined with the air film vents at the leading edge and blade tip, a three-dimensional cooling air film is formed over the entire area, eliminating cooling dead zones and greatly improving high temperature resistance and ablation resistance.

[0019] 2. Enhanced structural strength and reliability: The internal support ribs of the blades not only separate the flow channels but also significantly improve the stiffness, vibration resistance, and deformation resistance of the hollow blades. The blade tip diaphragm further strengthens the structure to meet the requirements of high-speed and high-load service.

[0020] 3. Maximize cooling gas utilization: The sealed inner cavity and independent flow channel design eliminate ineffective leakage of cooling gas, and force the air source to be supplied directionally to each air film hole, achieving higher cooling efficiency under the same air supply volume and reducing the energy loss of the whole machine.

[0021] 4. Precise, intuitive, and efficient testing: The matching testing fixtures closely simulate the actual assembly structure, ensuring reliable airway sealing, precise positioning, and stable air supply; the use of colored smoke visualization detection allows for quick assessment of air film pore patency, spray angle, and coverage effect, enabling efficient and accurate sorting of finished and defective products, and ensuring product quality consistency and safety in use.

[0022] 5. Strong structural adaptability and practicality: The overall structure is compact, the installation and positioning are reliable, the processing and assembly processes are good, and it is suitable for mass production and engineering applications, comprehensively improving the overall performance of turbine blades and the operational stability of equipment. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of the overall blade structure of this application; Figure 2 This is a schematic diagram of the internal structure of the blade in this application; Figure 3 This is an exploded structural diagram showing the relative positions of the components of the testing fixture in this application; Figure 4 This is a schematic diagram of the cross-section of the testing fixture in this application; Figure 5 This is a flowchart illustrating the detection method of this application.

[0025] The annotations in the attached figures are explained as follows: 1. Mounting base; 2. Connecting tenon; 3. Air inlet; 4. Blade body; 41. Pressure-bearing side; 42. Back pressure side; 5. Support rib; 6. Blade tip septum; 7. Film cooling hole; 8. Flow passage; 9. Turbine disk; 10. Connecting rivet groove; 11. Front retaining ring; 12. Front retaining ring; 13. Rear retaining ring; 14. Rear retaining ring; 15. Connecting hole; 16. Connecting groove; 17. Guide hole; 18. Air inlet groove; 19. Shaft hole; 20. Front fixing hole; 21. Front mounting hole; 22. Rear fixing hole; 23. Rear mounting hole; 24. Main air passage; 25. Bypass air passage; 26. Limiting protrusion; 27. Mounting shaft; 28. Seal. Detailed Implementation

[0026] In the description of this application, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are used only for the convenience of describing this application and 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, and therefore should not be construed as a limitation on this application. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this application, unless otherwise stated, "a plurality of" means two or more.

[0027] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art will understand the specific meaning of the above terms in this application based on the specific circumstances.

[0028] The following description, in conjunction with the accompanying drawings, further illustrates this application: Example

[0029] like Figures 1-2 As shown, an optimized structure for the air film pores on the surface of a worm gear blade includes a fixed base 1, an air inlet 3 on one side of the fixed base 1, and a connecting tenon 2 at the bottom of the fixed base 1. A blade body 4 is provided on the top of the fixed base 1. One side wall of the blade body 4 is a concave pressure-bearing side 41, and the other opposite side wall is a convex back pressure side 42.

[0030] Several sets of film gas holes 7 are provided on the pressure-bearing side 41, and each film gas hole 7 on the pressure-bearing side 41 faces the trailing edge of the blade body 4. This design allows the airflow to form a protective film along the blade surface, effectively reducing the thermal shock of the high-temperature airflow to the blade surface and improving the service life of the blade. A cavity is provided inside the blade body 4, and several supporting ribs 5 are provided inside the cavity of the blade body 4. The supporting ribs 5 divide the cavity inside the blade body 4 into several flow channels 8.

[0031] Each group of film cooling holes 7 is connected to several flow channels 8, and each flow channel 8 is connected to the air inlet 3. This structural design allows cooling gas to enter from the air inlet 3 and be evenly distributed to each group of film cooling holes 7 through the flow channels 8, forming a uniform cooling effect. A blade tip baffle 6 is fixedly installed on the top of several supporting stiffeners 5, and the blade tip baffle 6 is connected to the inner cavity sidewall of the blade body 4. The blade tip baffle 6 enhances the overall rigidity of the blade and also helps guide the cooling airflow.

[0032] In a preferred embodiment, film cooling holes 7 are also provided at the leading edge of the blade tip septum 6 and the blade body 4. These additional film cooling holes 7 can provide extra cooling protection for the leading edge region of the blade, since the leading edge of the blade is usually the area most severely impacted by high-temperature airflow, and adding film cooling holes 7 can significantly improve the cooling effect in this area.

[0033] The inspection fixture for detecting the optimized structure of the film cooling holes 7 on the surface of the worm gear blade includes a turbine disk 9. A shaft hole 19 is opened in the middle of the turbine disk 9, and an air inlet groove 18 is opened on the inner wall of the shaft hole 19. Several connecting riveting grooves 10 are evenly opened on the side wall of the turbine disk 9. The connecting riveting grooves 10 match the connecting tenons 2. This design allows the blade to be firmly installed on the turbine disk 9 for inspection.

[0034] A front retaining ring 11 is provided on one end face of the turbine disk 9, and a front retaining ring 12 is detachably mounted on the front retaining ring 11. A rear retaining ring 13 is provided on the other end face of the turbine disk 9, and a connecting groove 16 is formed on the rear retaining ring 13. The connecting groove 16 is connected to the air intake groove 18 through several guide holes 17 formed inside the turbine disk 9. This structural design ensures that the airflow can flow smoothly from the air intake groove 18 to the connecting groove 16, providing conditions for subsequent airflow testing.

[0035] A rear retaining ring 14 is detachably mounted on the rear fixed ring 13. One end face of the rear retaining ring 14 has a connecting hole 15, and the other end of the connecting hole 15 is located on the inner wall of the rear retaining ring 14. When the blade body 4 is connected to the turbine disk 9, the connecting tenon 2 is located between the front retaining ring 12 and the rear retaining ring 14. One end of the connecting hole 15 on the rear retaining ring 14 is connected to the air inlet 3, and the other end is connected to the connecting groove 16. This design ensures that the test gas can enter the air inlet 3 of the blade from the connecting groove 16 through the connecting hole 15, simulating the airflow path under actual working conditions.

[0036] The testing fixture also includes a mounting shaft 27, on which a limiting protrusion 26 is fixedly installed. A main air passage 24 is formed on one end face of the mounting shaft 27, and a bypass air passage 25 is formed on the mounting shaft 27 on one side of the limiting protrusion 26, communicating with the main air passage 24. When the turbine disk 9 is detachably connected to the mounting shaft 27 through the shaft hole 19, and when the turbine disk 9 is fitted onto the mounting shaft 27 and fits against the limiting protrusion 26, the bypass air passage 25 communicates with the inlet slot 18. This design allows the test gas to enter the inlet slot 18 from the main air passage 24 through the bypass air passage 25, and then flow to the various film cooling holes 7 inside the blade, achieving comprehensive testing of the blade's film cooling effect.

[0037] A plurality of front fixing holes 20 are formed on the front fixing ring 11, and a number of front mounting holes 21, the same number as the front fixing holes 20, are formed on the front retaining ring 12. After the front retaining ring 12 is fitted onto the front fixing ring 11, the front retaining ring 12 and the front fixing ring 11 are fixedly connected by passing bolts through the front mounting holes 21 and screwing them into the front fixing holes 20. This detachable connection method facilitates the assembly and disassembly of the tooling and improves the inspection efficiency.

[0038] The rear retaining ring 13 has several rear retaining holes 22, and the rear retaining ring 14 has the same number of rear mounting holes 23 as the rear retaining holes 22. After the rear retaining ring 14 is fitted onto the front retaining ring 11, the rear retaining ring 14 and the rear retaining ring 13 are fixedly connected by passing bolts through the rear mounting holes 23 and screwing them into the rear retaining holes 22. This design is the same as the connection method of the front retaining ring 12, ensuring the consistency and stability of the entire tooling structure.

[0039] Sealing elements 28 are provided at both ends of the air inlet groove 18 and the connecting groove 16. The sealing elements 28 can effectively prevent test gas leakage, ensure the accuracy and reliability of test data, and also improve the airtightness of the entire testing system.

[0040] The optimized structure of the film cooling holes 7 on the entire worm gear blade surface and the design of its testing fixture can effectively improve the cooling effect and service life of the worm gear blade. At the same time, the cooling effect of the film cooling holes 7 on the blade can be accurately evaluated through the special testing fixture, providing an important reference for the design optimization of the blade. Example

[0041] like Figures 3-4 As shown, the worm gear blade film perforation structure inspection fixture includes a turbine disk 9, with a shaft hole 19 in the center of the turbine disk 9 and an air inlet groove 18 on the inner wall of the shaft hole 19. Several connecting riveting grooves 10 are evenly provided on the side wall of the turbine disk 9, and these connecting riveting grooves 10 match the connecting tenons 2.

[0042] A front retaining ring 11 is provided on one end face of the turbine disk 9, and a front retaining ring 12 is detachably mounted on the front retaining ring 11. The front retaining ring 11 is bolted to the turbine disk 9 to ensure a secure connection. The front retaining ring 12 is connected to the front retaining ring 11 using a snap-fit ​​structure for easy and quick installation and removal. The inner diameter of the front retaining ring 12 is slightly smaller than the outer diameter of the turbine disk 9, forming a limiting structure to prevent axial displacement of the blades during testing.

[0043] A rear retaining ring 13 is provided on the other end face of the turbine disk 9, and a connecting groove 16 is formed on the rear retaining ring 13. The connecting groove 16 is connected to the air inlet groove 18 through a number of guide holes 17 formed inside the turbine disk 9. The guide holes 17 are radially distributed to ensure that the gas can flow evenly to each detection position. The diameter of the guide holes 17 gradually decreases, from 5 mm to 3 mm from the end near the air inlet groove 18 to the end of the connecting groove 16. This design can ensure that the gas pressure remains relatively stable during the flow process.

[0044] A rear retaining ring 14 is detachably mounted on the rear fixed ring 13, and a connecting hole 15 is provided on one end face of the rear retaining ring 14. The other end of the connecting hole 15 is located on the inner wall of the rear retaining ring 14. The rear retaining ring 14 is connected to the rear fixed ring 13 by a threaded connection, which facilitates adjustment of the installation position and disassembly. The connecting hole 15 is designed with a conical structure, with the larger end facing the end face of the rear retaining ring 14 and the smaller end facing the inner wall. This design is conducive to a smooth airflow transition and reduces turbulence generation.

[0045] After the blade body 4 is connected to the turbine disk 9, the connecting tenon 2 is located between the front retaining ring 12 and the rear retaining ring 14. One end of the connecting hole 15 on the rear retaining ring 14 is connected to the air inlet 3, and the other end is connected to the connecting groove 16. This design forms a complete air path system, allowing the detection gas to enter from the air inlet 3, pass through the connecting hole 15, the connecting groove 16, the guide hole 17, and the air inlet groove 18, and finally reach the blade film vent 7 structure that needs to be detected.

[0046] During use, firstly, the connecting tenon 2 of the blade body 4 is inserted into the connecting rivet groove 10 of the turbine disk 9. Then, the front retaining ring 12 and the rear retaining ring 14 are installed to form a sealed testing space. Testing gas at a specific pressure is injected into the system through the connecting hole 15. The gas flows along a preset gas path and is finally discharged through the film gas hole 7 structure on the blade. By observing the gas flow or using professional testing instruments to measure changes in gas flow rate and pressure, it can be determined whether the blade film gas hole 7 structure meets the design requirements and whether there are any problems such as blockage or deformation.

[0047] The structural design of this inspection fixture makes the inspection process of the blade film cooling holes 7 more accurate and reliable, and can comprehensively evaluate the quality of the blade film cooling holes 7. At the same time, the detachable front retaining ring 12 and rear retaining ring 14 design makes the fixture highly adaptable and suitable for the inspection of worm gear blades of different specifications and models.

[0048] In a preferred embodiment, the turbine disk 9 is made of high-strength aluminum alloy, which is lightweight and high-strength, making it easy for operators to handle and use. The front retaining ring 11 and the rear retaining ring 13 are made of stainless steel, which has good corrosion resistance and wear resistance, extending the service life of the tooling.

[0049] In another preferred embodiment, a sealing ring is provided on the inner wall of the connection hole 15 on the rear retaining ring 14 to ensure that gas does not leak from the connection during the detection process, thereby improving the accuracy of the detection. The sealing ring is made of high-temperature resistant silicone material, which can adapt to the detection requirements under different temperature environments. Example

[0050] like Figure 5 As shown, the inspection method of the inspection fixture includes the following steps: S1. Front retaining ring 12 installation: Install the front retaining ring 12 onto the front retaining ring 11 and secure it. The front retaining ring 11 is located on one end face of the turbine disk 9. The front retaining ring 12 and the front retaining ring 11 are fixed by bolts to ensure that the two fit tightly and will not loosen or leak during subsequent testing.

[0051] S2. Blade Body 4 Installation: Install the blade body 4 onto the turbine disk 9, ensuring that the end of the mounting base 1 of the blade body 4 without the air inlet 3 is flush with the front retaining ring 12. The blade body 4 includes a mounting base 1, with an air inlet 3 on one side and a connecting tenon 2 at the bottom. The blade body 4 is mounted on the top, with one side wall being a concave pressure-bearing side 41 and the opposite side wall being a convex back pressure side 42. Several sets of film gas holes 7 are formed on the pressure-bearing side 41, each facing the trailing edge of the blade body 4. The blade body 4 has an internal cavity, within which several supporting ribs 5 are provided, dividing the cavity into several flow channels 8. Each set of film gas holes 7 is connected to several flow channels 8, and each flow channel 8 is connected to the air inlet 3. A blade tip baffle 6 is fixedly installed on the top of several supporting stiffeners 5, and the blade tip baffle 6 is connected to the inner cavity side wall of the blade body 4. The connecting tenon 2 of the blade body 4 is inserted into the connecting rivet grooves 10 evenly opened on the side wall of the turbine disk 9 to ensure that the connecting tenon 2 matches the connecting rivet groove 10, so as to achieve a stable connection between the blade body 4 and the turbine disk 9.

[0052] S3. Rear retaining ring 14 installation: Install the rear retaining ring 14 onto the rear fixing ring 13 and secure it. The rear fixing ring 13 is located on the other end face of the turbine disk 9. A connecting groove 16 is provided on the rear fixing ring 13. The connecting groove 16 is connected to the air intake groove 18 on the inner wall of the shaft hole 19 in the middle of the turbine disk 9 through several guide holes 17 opened inside the turbine disk 9. A connecting hole 15 is provided on one end face of the rear retaining ring 14, and the other end of the connecting hole 15 is located on the inner wall of the rear retaining ring 14. After the blade body 4 is connected to the turbine disk 9, the connecting tenon 2 is located between the front retaining ring 12 and the rear retaining ring 14. One end of the connecting hole 15 on the rear retaining ring 14 is connected to the air intake hole 3, and the other end is connected to the connecting groove 16. The rear retaining ring 14 and the rear fixing ring 13 are fastened together with bolts to form a detection device with good airtightness.

[0053] S4. Connection of mounting shaft 27: Connect the turbine disk 9 to the mounting shaft 27. The mounting shaft 27 passes through the shaft hole 19 of the turbine disk 9 and fits tightly with the shaft hole 19. The mounting shaft 27 is provided with a main air passage 24, which is connected to the air inlet groove 18 on the inner wall of the shaft hole 19 of the turbine disk 9, forming a complete gas flow path.

[0054] S5. Smoke Input and Observation: Introduce colored smoke into the main air duct 24 on the mounting shaft 27, allowing it to flow through the following path: after exiting the main air duct 24, it flows sequentially through the inlet slot 18, guide hole 17, connecting slot 16, connecting hole 15, inlet hole 3, and flow passage 8 before exiting through the film gas hole 7. Observe the flow state of the gas exiting the film gas hole 7 on the surface of the blade body 4, paying particular attention to whether the airflow distribution at the outlet of the film gas hole 7 is uniform and whether the airflow can adhere to the blade surface to form an effective film gas protective layer.

[0055] S6. Classification and Judgment: Based on the flow state of the colored gas on the surface of the blade body 4, finished products and defective products are classified. The standard for finished products is: the gas flows out uniformly from the gas film holes 7, forming a continuous and uniform gas film covering layer on the blade surface, and the airflow flows smoothly along the blade surface to the trailing edge without obvious flow interruption or eddy phenomena; the characteristics of defective products are: the gas flows out unevenly from the gas film holes 7, some gas film holes 7 are blocked or deformed, the gas film formed by the airflow on the blade surface is discontinuous, obvious airflow separation or local eddy phenomena occur, and an effective thermal protection layer cannot be formed.

[0056] The above testing methods allow for a direct observation of the working state of the air film pore 7 structure on the blade, effectively evaluating the design and manufacturing quality of the air film pore 7, and ensuring that the worm gear blade can obtain good air film cooling protection in a high-temperature working environment.

[0057] The foregoing has provided a detailed description of one embodiment of this application, but the description is merely a preferred embodiment and should not be construed as limiting the scope of this application. All equivalent variations and improvements made within the scope of this application should still fall within the patent coverage of this application.

Claims

1. An optimized structure and inspection fixture for film pores on the surface of a worm gear blade, characterized in that: The optimized structure of the air film perforation on the surface of the worm gear blade includes a fixed base (1), an air inlet (3) is provided on one side of the fixed base (1), a connecting tenon (2) is provided at the bottom of the fixed base (1), and a blade body (4) is provided on the top of the fixed base (1). One side wall of the blade body (4) is a concave pressure-bearing side (41), and the other opposite side wall is a convex back pressure side (42). Several sets of air film perforations (7) are opened on the pressure-bearing side (41), and each air film perforation (7) on the pressure-bearing side (41) faces the blade body (4). The trailing edge of the blade body (4) has a cavity inside. Several supporting ribs (5) are provided in the cavity of the blade body (4). The supporting ribs (5) divide the cavity inside the blade body (4) into several flow channels (8). Each group of air film holes (7) is connected to several flow channels (8) respectively. Each flow channel (8) is connected to the air inlet (3). A blade tip baffle (6) is fixedly provided on the top of the supporting ribs (5). The blade tip baffle (6) is connected to the inner cavity sidewall of the blade body (4). The inspection fixture for detecting the optimized structure of the air film pores on the surface of the worm gear blades includes a turbine disk (9), a shaft hole (19) in the middle of the turbine disk (9), an air inlet groove (18) on the inner wall of the shaft hole (19), and a plurality of connecting riveting grooves (10) evenly distributed on the side wall of the turbine disk (9), the connecting riveting grooves (10) matching the connecting tenon (2). A front fixing ring (11) is provided on one end face of the turbine disk (9), a front retaining ring (12) is detachably provided on the front fixing ring (11), and a rear fixing ring (13) is provided on the other end face of the turbine disk (9), the rear fixing ring (13) having a connecting groove (16). The connecting groove (16) and the air intake groove (18) are connected through a plurality of guide holes (17) opened inside the turbine disk (9). A rear retaining ring (14) is detachably provided on the rear fixing ring (13). A connecting hole (15) is also provided on one end face of the rear retaining ring (14). The other end of the connecting hole (15) is located on the inner wall of the rear retaining ring (14). When the blade body (4) is connected to the turbine disk (9), the connecting tenon (2) is located between the front retaining ring (12) and the rear retaining ring (14). One end of the connecting hole (15) on the rear retaining ring (14) is connected to the air intake hole (3), and the other end is connected to the connecting groove (16).

2. The optimized structure and inspection fixture for the air film pores on the surface of a worm gear blade according to claim 1, characterized in that: Air film holes (7) are also provided at the leading edge of the blade tip septum (6) and the blade body (4).

3. The optimized structure and testing fixture for film pores on the surface of a worm gear blade according to claim 1, characterized in that: The testing fixture also includes a mounting shaft (27), on which a limiting protrusion (26) is fixedly provided. A main air passage (24) is provided on one end face of the mounting shaft (27), and a bypass air passage (25) is provided on the mounting shaft (27) on one side of the limiting protrusion (26). The bypass air passage (25) is connected to the main air passage (24). When the turbine disk (9) is detachably connected to the mounting shaft (27) through the shaft hole (19), and when the turbine disk (9) is fitted onto the mounting shaft (27) and fits against the limiting protrusion (26), the bypass air passage (25) is connected to the air inlet groove (18).

4. The optimized structure and inspection fixture for the air film pores on the surface of a worm gear blade according to claim 1, characterized in that: A plurality of front fixing holes (20) are provided on the front fixing ring (11), and a number of front mounting holes (21) are provided on the front retaining ring (12) in the same number as the front fixing holes (20). After the front retaining ring (12) is fitted onto the front fixing ring (11), the front retaining ring (12) and the front fixing ring (11) are fixedly connected by passing a bolt through the front mounting hole (21) and screwing it into the front fixing hole (20). A plurality of rear fixing holes (22) are provided on the rear fixing ring (13), and a number of rear mounting holes (23) are provided on the rear retaining ring (14) in the same number as the rear fixing holes (22). After the rear retaining ring (14) is fitted onto the front fixing ring (11), the rear retaining ring (14) and the rear fixing ring (13) are fixedly connected by passing a bolt through the rear mounting hole (23) and screwing it into the rear fixing hole (22).

5. The optimized structure and inspection fixture for the air film pores on the surface of a worm gear blade according to claim 1, characterized in that: Sealing elements (28) are provided at both ends of the air inlet groove (18) and the connecting groove (16).

6. A detection method based on the detection fixture for the optimized structure of film pores on the surface of a worm gear blade as described in claim 1, characterized in that, Includes the following steps: S1, Install the front retaining ring (12) onto the front fixing ring (11) and fix it; S2, install the blade body (4) onto the turbine disk (9), and make the end of the fixed seat (1) of the blade body (4) without the air inlet (3) fit against the front baffle (12); S3, install the rear retaining ring (14) onto the rear retaining ring (13) and fix it. After the rear retaining ring (14) and the rear retaining ring (13) are fitted together, the connecting hole (15) will connect the connecting groove (16) with the air intake (3). Then connect the turbine disk (9) to the mounting shaft (27). S4. Introduce colored smoke into the main air passage (24) on the mounting shaft (27) and let it flow out from the air film hole (7) on the blade body (4). Observe the flow state of the gas flowing out from the air film hole (7) on the surface of the blade body (4). Classify the finished product and the defective product according to the flow state of the colored gas on the surface of the blade body (4).

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