Aero-engine turbine guide vane thermal stress release groove processing device and processing method

Abstract

The application discloses an aero-engine turbine guide vane thermal stress release groove processing device, and a processing device thereof. The processing device comprises an electrode chuck, a positioning clamp and a profiling electrode. The electrode chuck comprises a connecting piece for connecting a processing machine tool and a clamping piece for profiling and clamping the profiling electrode connected with the connecting piece. The positioning clamp comprises a support and a positioning piece for clamping the turbine guide vane rotatably arranged on the support. A plurality of positioning holes are arranged on the positioning piece in a circumferential direction of the positioning piece and are arranged on the positioning piece in a radial direction of the turbine guide vane to be machined. The plurality of positioning holes are arranged on the positioning piece in the circumferential direction of the positioning piece. A fixing hole is arranged on the support in an axial direction of the positioning hole. The positioning clamp further comprises a fixing pin for fixing the positioning piece to the support. The application further discloses an aero-engine turbine guide vane thermal stress release groove processing method.

Description

Machining apparatus and method for thermal stress relief grooves of aero-engine turbine guide vanes Technical Field

[0001] This invention relates to the field of aero-engine component processing technology, and in particular, to a processing apparatus for thermal stress relief grooves in aero-engine turbine guide vanes. Furthermore, this invention also relates to a processing method for thermal stress relief grooves in aero-engine turbine guide vanes using the aforementioned processing apparatus. Background Technology

[0002] Currently, in small and medium-sized aero engines, turbine guide vanes are mostly integrally cast using a casting process. To reduce manufacturing complexity, these turbine guide vanes typically do not incorporate cooling structures during casting. However, when operating in a high-temperature, high-pressure environment for extended periods, the inconsistent temperature and pressure experienced by the inner and outer rings can easily lead to ductile cracks at stress concentration points on the inner ring, thus affecting the safe operation of the aero engine. Therefore, to improve the service life and performance of integrally cast turbine guide vanes, thermal stress relief grooves are generally designed and machined between the blades on the inner ring to balance the high temperature and high pressure experienced by the inner and outer rings.

[0003] For example, Chinese invention patent application CN115091210A discloses a method for processing a power turbine guide. The power turbine guide includes an outer ring, an inner ring, and a honeycomb structure. The outer ring and the inner ring are connected by guide blades. The inner ring is provided with multiple bosses and multiple heat stress relief grooves. The outer ring has multiple precision bosses. The characteristic is that the axial dimension of the inner ring mounting edge is reserved. After the heat stress relief grooves on the inner ring are processed, the axial dimension of the inner ring mounting edge is then precision machined to the required position.

[0004] However, since the inner annular flow channel of a turbine guide vane is often part of the internal flow channel of an aero-engine, machining thermal stress relief grooves on the flow channel of an aero-engine requires avoiding the guide vanes, making the machining process difficult. The thermal stress relief grooves themselves are non-linear and not fixed in structure, generally having large rounded corners or bending areas. They can usually only be formed using a contour electrode through electrical discharge machining (EDM). However, most thermal stress relief grooves are very narrow, with a width of only 0.1-0.3 mm, and the corresponding contour electrodes are even thinner. During machining, they are prone to deformation due to improper storage or clamping methods. Furthermore, the spatial angles of the stress relief grooves on the inner ring of the turbine guide vane are complex and difficult to control. Therefore, with existing machining methods, the machining efficiency of thermal stress relief grooves is low, and the machining quality is unstable, failing to meet the design and production requirements of turbine guide vanes. Summary of the Invention

[0005] This invention provides a processing device and method for processing thermal stress relief grooves for aero-engine turbine guide vanes, in order to solve the technical problems of existing processing methods for thermal stress relief grooves, such as easy deformation of the conforming electrode and difficulty in controlling the spatial angle of the turbine guide vane, resulting in high processing difficulty and unstable processing quality.

[0006] According to one aspect of the present invention, a processing apparatus for thermal stress relief grooves of an aero-engine turbine guide is provided, for processing thermal stress relief grooves on a turbine guide. The turbine guide has a plurality of thermal stress relief grooves to be processed arranged circumferentially at intervals. The processing apparatus includes an electrode chuck, a positioning fixture, and a contour electrode. The electrode chuck includes a connector for connecting to a machine tool and a clamping member connected to the connector for contour clamping the contour electrode. The positioning fixture includes a support member and a positioning member rotatably arranged on the support member for clamping the turbine guide. The positioning member has a plurality of positioning holes arranged circumferentially at intervals on the positioning member and corresponding radially to the thermal stress relief grooves to be processed on the turbine guide. The plurality of positioning holes are arranged circumferentially at intervals on the positioning member and are arranged one-to-one with the thermal stress relief grooves to be processed. The support member has fixing holes corresponding axially to the positioning holes. The positioning fixture also includes a fixing pin for axially passing through the positioning holes and fixing holes to fix the positioning member to the support member.

[0007] As a further improvement to the above technical solution:

[0008] Furthermore, the connector includes a connecting shaft, a reference plate for connecting the spindle of a machine tool fixedly connected to the first axial end of the connecting shaft, and a clearance plate for preventing interference between the contour electrode and the turbine guide, which are fixedly connected to the connecting shaft and the clamping member respectively. The length direction of the clearance plate is perpendicular to the axial direction of the connecting shaft, the first end of the clearance plate in the length direction is fixedly connected to the second axial end of the connecting shaft, and the second end of the clearance plate in the length direction is fixedly connected to the clamping member.

[0009] Furthermore, the clamping member includes a contouring connecting plate fixedly connected to the second end of the clearance plate in the length direction, and a contouring clamping plate connected to the contouring connecting plate for forming a contouring groove with the contouring connecting plate and pressing and fixing the contouring electrode in the contouring groove. The inner wall surface of the contouring groove matches the outer wall surface of the contouring electrode, and the opening direction of the contouring groove on the clamping member is opposite to the axial direction of the connecting shaft.

[0010] Furthermore, the second axial end of the connecting shaft is provided with a mounting edge that extends radially outward, and the connector also includes a connecting bolt that passes through the mounting edge and is threadedly connected to the clearance plate.

[0011] Furthermore, the support includes a bracket and a support plate fixedly arranged on the bracket and supporting the positioning component.

[0012] Furthermore, a tool setting block for aligning the conformal electrode is fixedly arranged on the support.

[0013] Furthermore, the positioning component includes a positioning plate rotatably arranged on the support plate for accommodating the turbine guide to achieve radial positioning of the turbine guide, an angular positioning pin connected to the positioning plate for passing through the turbine guide and the positioning plate to achieve angular positioning of the turbine guide, and a clamping structure for pressing the turbine guide to achieve axial positioning of the turbine guide, with positioning holes arranged on the positioning plate.

[0014] Furthermore, the clamping structure includes clamping holes on the positioning plate, clamping plates arranged corresponding to the clamping holes for pressing the turbine guide, and clamping bolts passing through the clamping plates and threadedly connected to the clamping holes. Multiple clamping holes are arranged at intervals along the circumference of the positioning plate, and the clamping holes, clamping plates, and clamping bolts are arranged in a one-to-one correspondence.

[0015] Furthermore, the pressing end of the clamping plate is made of copper.

[0016] According to another aspect of the present invention, a method for machining thermal stress relief grooves of aero-engine turbine guide vanes is also provided. This method utilizes the aforementioned machining apparatus for thermal stress relief grooves of aero-engine turbine guide vanes, specifically including the following steps: S1, fixing the turbine guide vane to a positioning member, then rotating the positioning member relative to a support member to align the positioning hole with the fixing hole, and finally inserting a fixing pin into the positioning hole and the fixing hole; S2, clamping a contour electrode using a clamping member, straightening the contour electrode, and then connecting it to a machining tool via a connecting member; S3, aligning the contour electrode and moving it to the machining position to machine the thermal stress relief groove corresponding to the positioning hole until the thermal stress relief groove is formed; S4, removing the fixing pin, then rotating the positioning member relative to the support member to align the next positioning hole with the fixing hole, then inserting the fixing pin into the positioning hole and the fixing hole, and finally moving the contour electrode to the machining position to machine the thermal stress relief groove corresponding to the positioning hole until the thermal stress relief groove is formed; S5, repeating step S4 until all the thermal stress relief grooves are formed.

[0017] The present invention has the following beneficial effects:

[0018] The present invention relates to a machining device for thermal stress relief grooves on aero-engine turbine guide vanes. An electrode chuck is connected to a machine tool via a connector, improving the fit between the electrode chuck and the machine tool and increasing machining accuracy. A shaped electrode is then clamped by a clamping member to enhance the rigidity of the shaped electrode and limit its clamping length, minimizing deformation caused by improper clamping and thus significantly improving machining quality. A positioning fixture reliably supports a positioning member via a support member, which then clamps the turbine guide vane. Multiple positioning holes are spaced circumferentially on the positioning member, and these holes are radially aligned with the thermal stress relief grooves to be machined on the turbine guide vane. This arrangement determines the spatial angle of the turbine guide vane by controlling the positioning holes. Simultaneously, fixing holes are axially aligned on the support member to... During processing, the positioning component is rotated on the support to align the positioning hole and the fixing hole in the axial direction. A fixing pin is then inserted axially to fix the positioning component to the support. Simultaneously, the position of the thermal stress relief groove to be processed on the turbine guide is determined, facilitating the movement of the electrode chuck to process the groove. The turbine guide is clamped by a positioning fixture, making it easy to move the contour electrode to the processing position, significantly improving processing efficiency. This solution uses the coordinated operation of the electrode chuck, contour electrode, and positioning fixture to process the thermal stress relief groove on the turbine guide. The electrode chuck clamps the contour electrode to prevent deformation, and the positioning fixture allows for easy control of the turbine guide's spatial angle. Compared to existing technologies, this significantly improves processing efficiency and ensures processing quality. It is highly practical and suitable for widespread promotion and application.

[0019] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0021] Figure 1 is a schematic diagram of the structure of the machining device for thermal stress relief groove of aero-engine turbine guide vane according to a preferred embodiment of the present invention;

[0022] Figure 2 is a partial structural schematic diagram of the machining device for thermal stress relief grooves of aero-engine turbine guide vanes according to a preferred embodiment of the present invention.

[0023] Legend:

[0024] 100. Electrode chuck; 110. Connecting shaft; 120. Reference plate; 130. Clearance plate; 140. Contouring connecting plate; 150. Contouring clamping plate; 200. Positioning fixture; 210. Positioning hole; 220. Bracket; 230. Support plate; 240. Tool setting block; 250. Positioning plate; 260. Angular positioning pin; 270. Clamping structure; 300. Contouring electrode. Detailed Implementation

[0025] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0026] Figure 1 is a schematic diagram of the structure of the thermal stress relief groove processing device for aero-engine turbine guide vanes according to a preferred embodiment of the present invention; Figure 2 is a partial schematic diagram of the structure of the thermal stress relief groove processing device for aero-engine turbine guide vanes according to a preferred embodiment of the present invention.

[0027] As shown in Figures 1 and 2, the aero-engine turbine guideway thermal stress relief groove processing apparatus of this embodiment is used to process thermal stress relief grooves on the turbine guideway. The turbine guideway has multiple thermal stress relief grooves to be processed arranged at intervals along the circumference. The processing apparatus includes an electrode chuck 100, a positioning fixture 200, and a contour electrode 300. The electrode chuck 100 includes a connector for connecting to a machine tool and a clamping member connected to the connector for contour clamping the contour electrode 300. The positioning fixture 200 includes a support member and a turbine guideway guideway clamping member rotatably arranged on the support member. The positioning component of the guide has multiple positioning holes 210 arranged at intervals along the circumference of the positioning component and corresponding radially to the thermal stress relief grooves to be processed on the turbine guide. The multiple positioning holes 210 are arranged at intervals along the circumference of the positioning component and are used to correspond one-to-one with the thermal stress relief grooves to be processed. The support has fixing holes that correspond axially to the positioning holes 210. The positioning clamp 200 also includes a fixing pin that passes through the positioning holes 210 and the fixing holes axially to fix the positioning component to the support.Specifically, in the aero-engine turbine guideway thermal stress relief groove processing device of the present invention, the electrode chuck 100 is connected to the machine tool via a connector, improving the fit between the electrode chuck 100 and the machine tool and increasing processing accuracy. Then, the conforming electrode 300 is clamped by a clamping member to increase the rigidity of the conforming electrode 300 and limit its clamping length, minimizing deformation caused by improper clamping and thus greatly improving processing quality. The positioning fixture 200 reliably supports the positioning member via a support member, and the turbine guideway is clamped by the positioning member. Multiple positioning holes 210 are spaced apart in the circumferential direction on the positioning member, and these positioning holes 210 are radially aligned with the thermal stress relief groove to be processed on the turbine guideway to determine the spatial angle of the turbine guideway controlled by the positioning holes 210. Simultaneously, fixing holes are formed in the support member that correspond axially to the positioning holes 210. During processing, the positioning member is rotated on the support to align the positioning hole 210 and the fixing hole in the axial direction. A fixing pin is then inserted axially to fix the positioning member to the support. Simultaneously, the position of the thermal stress relief groove to be processed on the turbine guide is determined, facilitating the movement of the electrode chuck 100 to process the thermal stress relief groove on the turbine guide. The turbine guide is clamped by the positioning fixture 200, making it easy to move the contour electrode 300 to the processing position, greatly improving processing efficiency. This solution uses the coordinated operation of the electrode chuck 100, the contour electrode 300, and the positioning fixture 200 to process the thermal stress relief groove on the turbine guide. The electrode chuck 100 contour-clamps the contour electrode 300 to prevent deformation, and the positioning fixture 200 makes it easy to control the spatial angle of the turbine guide. Compared to existing technologies, this solution greatly improves processing efficiency and ensures processing quality. It is highly practical and suitable for widespread promotion and application. It should be understood that existing indexing plates can only rotate to a fixed angle, while the angle between adjacent thermal stress relief grooves on a turbine guide is usually not an integer angle. If a driven indexing plate is used for spatial angle control of the turbine guide, angle deviations are likely to occur, resulting in low processing efficiency and unstable processing quality. In this embodiment, spatial angle control of the turbine guide is achieved through positioning holes 210 on the positioning member. Since the positioning holes 210 and the thermal stress relief grooves to be processed correspond radially, and the turbine guide is fixed by a fixing pin passing through the positioning holes 210 and the fixing holes, angle deviations can be avoided to the greatest extent, thereby improving processing efficiency and ensuring processing quality. It should be understood that in this embodiment, there is one fixing hole and multiple positioning holes 210. By rotating the positioning member, the multiple positioning holes 210 are sequentially aligned with the fixing hole in the axial direction.

[0028] As shown in Figure 2, in this embodiment, the connector includes a connecting shaft 110, a reference plate 120 for connecting the spindle of a machine tool, which is fixedly connected to the first axial end of the connecting shaft 110, and a clearance plate 130 for preventing interference between the contour electrode 300 and the turbine guide, which is fixedly connected to the connecting shaft 110 and the clamping member respectively. The length direction of the clearance plate 130 is perpendicular to the axial direction of the connecting shaft 110, the first end of the clearance plate 130 in the length direction is fixedly connected to the second axial end of the connecting shaft 110, and the second end of the clearance plate 130 in the length direction is fixedly connected to the clamping member. Specifically, the first axial end of the connecting shaft 110 is connected to the spindle of the machining tool via the reference plate 120, enabling rapid switching between the electrode chuck 100 and the spindle of the machining tool. This helps reduce the clamping error of the contour electrode 300 and improves machining accuracy. Furthermore, by making the length direction of the clearance plate 130 perpendicular to the axial direction of the connecting shaft 110, the second axial end of the connecting shaft 110 is connected to the first end of the length direction of the clearance plate 130. The second end of the length direction of the clearance plate 130 is connected to the clamping member. This allows the contour electrode 300 in the clamping member to avoid the turbine guide via the clearance plate 130, preventing interference between the contour electrode 300 and the turbine guide and greatly improving machining efficiency.

[0029] As shown in Figure 2, in this embodiment, the clamping member includes a contouring connecting plate 140 fixedly connected to the second end of the clearance plate 130 along its length, and a contouring pressing plate 150 connected to the contouring connecting plate 140 for forming a contouring groove with the contouring connecting plate 140 and pressing and fixing the contouring electrode 300 in the contouring groove. The inner wall surface of the contouring groove matches the outer wall surface of the contouring electrode 300, and the opening direction of the contouring groove on the clamping member is opposite to the axial direction of the connecting shaft 110. Specifically, the clamping member is connected to the second end of the clearance plate 130 in the length direction through the contouring connecting plate 140, and then the contouring clamping plate 150 and the contouring connecting plate 140 are used to form a contouring groove and press and fix the contouring electrode 300 in the contouring groove. Since the inner wall surface of the contouring groove matches the outer wall surface of the contouring electrode 300, it prevents the contouring electrode 300 from deforming when clamped. At the same time, since the opening direction of the contouring groove on the clamping member is opposite to the axial direction of the connecting shaft 110, the contouring electrode 300 extends away from the connecting shaft 110 to facilitate the processing of the thermal stress relief groove.

[0030] As shown in Figure 2, in this embodiment, the second axial end of the connecting shaft 110 is provided with a mounting edge extending radially outward, and the connector also includes a connecting bolt passing through the mounting edge and threadedly connected to the clearance plate 130. Specifically, the connecting shaft 110 is reliably connected to the clearance plate 130 through the mounting edge and the connecting bolt.

[0031] As shown in Figure 1, in this embodiment, the support includes a bracket 220 and a support plate 230 fixedly arranged on the bracket 220 and supporting the positioning component. Specifically, the support plate 230 is reliably installed on the bracket 220, and the positioning component is supported by the support plate 230.

[0032] As shown in Figure 1, in this embodiment, a tool setting block 240 for aligning the contour electrode 300 is fixedly arranged on the bracket 220. Specifically, before processing, the contour electrode 300 is aligned by the tool setting block 240, and then the contour electrode 300 is moved to the processing position, so as to greatly reduce the alignment error and improve the processing stability and the dimensional pass rate.

[0033] As shown in Figure 1, in this embodiment, the positioning component includes a positioning plate 250 rotatably mounted on a support plate 230 for accommodating the turbine guide to achieve radial positioning of the turbine guide; an angular positioning pin 260 passing through the turbine guide and the positioning plate 250 to achieve angular positioning of the turbine guide; and a clamping structure 270 connected to the positioning plate 250 for pressing the turbine guide to achieve axial positioning of the turbine guide. Positioning holes 210 are arranged on the positioning plate 250. Specifically, the turbine guide is radially positioned by accommodating it through the positioning plate 250, angularly positioned by the angular positioning pin 260, and finally axially positioned by the clamping structure 270, thereby reliably fixing the turbine guide in the positioning component. By ensuring reliable clamping, the processing quality is improved.

[0034] As shown in Figure 1, in this embodiment, the clamping structure 270 includes clamping holes formed on the positioning plate 250, clamping plates corresponding to the clamping holes for pressing against the turbine guide, and clamping bolts passing through the clamping plates and threadedly connected to the clamping holes. Multiple clamping holes are arranged at intervals along the circumference of the positioning plate 250, and the clamping holes, clamping plates, and clamping bolts are arranged in a one-to-one correspondence. Specifically, the clamping bolts pass through the clamping plates and are threadedly connected to the clamping holes to press against the clamping plates, thereby causing the clamping plates to press against the turbine guide, achieving axial positioning of the turbine guide. Furthermore, the synchronous pressing by the circumferentially spaced clamping plates ensures reliable axial positioning of the turbine guide.

[0035] As shown in Figure 1, in this embodiment, the pressing end of the clamping plate is made of copper. It should be understood that turbine guides are usually made of high-strength metals, while copper is relatively soft. Therefore, when clamping and fixing the turbine guide, damage can be avoided, ensuring the quality of the turbine guide.

[0036] As shown in Figures 1 and 2, the machining method for the thermal stress relief groove of the aero-engine turbine guide in this embodiment uses the aforementioned machining device for the thermal stress relief groove of the aero-engine turbine guide. Specifically, it includes the following steps: S1, fixing the turbine guide on the positioning member, then rotating the positioning member relative to the support member to align the positioning hole 210 with the fixing hole, and finally inserting the fixing pin into the positioning hole 210 and the fixing hole; S2, clamping the contour electrode 300 using the clamping member, straightening the contour electrode 300, and then connecting it to the machining machine tool using the connecting member; S3, aligning the contour electrode 300 and moving it... The contour electrode 300 is moved to the machining position to machine the thermal stress relief groove corresponding to the positioning hole 210 until the thermal stress relief groove is formed; S4, the fixing pin is pulled out, and then the positioning member is rotated relative to the support member to align the next positioning hole 210 with the fixing hole. The fixing pin is then inserted into the positioning hole 210 and the fixing hole. Finally, the contour electrode 300 is moved to the machining position to machine the thermal stress relief groove corresponding to the positioning hole 210 until the thermal stress relief groove is formed; S5, step S4 is repeated until all the thermal stress relief grooves are formed. Specifically, through the cooperation between the contour electrode 300, the electrode chuck 100 and the positioning fixture 200, the deformation of the contour electrode 300 is improved, and the groove angle between two adjacent thermal stress relief grooves is controlled, which greatly improves the stability of the machining process, reduces the error caused by repeated clamping and alignment, and reduces the risk of out-of-tolerance. Optionally, in one embodiment, the width of the thermal stress relief groove is 0.2±0.1mm, and the groove angles between two adjacent thermal stress relief grooves are 76°22′±40′ and 65°27′±40′, respectively.

[0037] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A processing apparatus for thermal stress relief grooves on an aero-engine turbine guide vane, used to process thermal stress relief grooves on a turbine guide vane, wherein the turbine guide vane is provided with a plurality of thermal stress relief grooves to be processed arranged at intervals along the circumference, characterized in that, The processing device includes an electrode chuck (100), a positioning fixture (200), and a contour electrode (300). The electrode chuck (100) includes a connector for connecting to a machine tool and a clamping member connected to the connector for contour clamping the contour electrode (300). The positioning fixture (200) includes a support member and a positioning member rotatably arranged on the support member for clamping a turbine guide. The positioning member has multiple positioning holes (210) spaced apart along the circumference of the positioning member and arranged radially corresponding to the thermal stress relief grooves to be processed on the turbine guide. The multiple positioning holes (210) are spaced apart along the circumference of the positioning member and are arranged one-to-one with the thermal stress relief grooves to be processed. The support member has a corresponding positioning hole (210). The positioning fixture (200) also includes a fixing pin for fixing the positioning member to the support member by passing through the positioning hole (210) and the fixing hole along the axial direction; the connecting member includes a connecting shaft (110), a reference plate (120) for connecting the spindle of the machining tool and fixedly connected to the first axial end of the connecting shaft (110), and a relief plate (130) for preventing the contour electrode (300) and the turbine guide from interfering with each other and fixedly connected to the connecting shaft (110) and the clamping member respectively. The length direction of the relief plate (130) is perpendicular to the axial direction of the connecting shaft (110), the first end of the relief plate (130) in the length direction is fixedly connected to the second axial end of the connecting shaft (110), and the second end of the relief plate (130) in the length direction is fixedly connected to the clamping member.

2. The apparatus for machining thermal stress relief grooves for aero-engine turbine guide vanes according to claim 1, characterized in that, The clamping member includes a contouring connecting plate (140) fixedly connected to the second end of the clearance plate (130) in the longitudinal direction, and a contouring clamping plate (150) connected to the contouring connecting plate (140) for forming a contouring groove with the contouring connecting plate (140) and pressing and fixing the contouring electrode (300) in the contouring groove. The inner wall surface of the contouring groove matches the outer wall surface of the contouring electrode (300), and the opening direction of the contouring groove on the clamping member is opposite to the axial direction of the connecting shaft (110).

3. The apparatus for machining thermal stress relief grooves for aero-engine turbine guide vanes according to claim 1, characterized in that, The second axial end of the connecting shaft (110) is provided with a mounting edge that extends radially outward, and the connector also includes a connecting bolt that passes through the mounting edge and is threadedly connected to the relief plate (130).

4. The apparatus for machining thermal stress relief grooves for aero-engine turbine guide vanes according to any one of claims 1-3, characterized in that, The support includes a bracket (220) and a support plate (230) fixedly arranged on the bracket (220) and supporting the positioning component.

5. The apparatus for machining thermal stress relief grooves for aero-engine turbine guide vanes according to claim 4, characterized in that, The support (220) is fixedly equipped with a tool setting block (240) for aligning the conforming electrode (300).

6. The apparatus for machining thermal stress relief grooves for aero-engine turbine guide vanes according to claim 4, characterized in that, The positioning components include a positioning plate (250) rotatably mounted on a support plate (230) for accommodating a turbine guide to achieve radial positioning of the turbine guide, an angular positioning pin (260) connected to the positioning plate (250) for passing through the turbine guide and the positioning plate (250) to achieve angular positioning of the turbine guide, and a clamping structure (270) for clamping the turbine guide to achieve axial positioning of the turbine guide, with positioning holes (210) arranged on the positioning plate (250).

7. The apparatus for machining thermal stress relief grooves for aero-engine turbine guide vanes according to claim 6, characterized in that, The clamping structure (270) includes clamping holes opened on the positioning plate (250), clamping plates arranged corresponding to the clamping holes for pressing the turbine guide, and clamping bolts passing through the clamping plates and threadedly connected to the clamping holes. Multiple clamping holes are arranged at intervals along the circumference of the positioning plate (250), and the clamping holes, clamping plates and clamping bolts are arranged one-to-one.

8. The apparatus for machining thermal stress relief grooves for aero-engine turbine guide vanes according to claim 7, characterized in that, The pressing end of the clamping plate is made of copper.

9. A method for machining a thermal stress relief groove in an aero-engine turbine guide vane, characterized in that, The machining of the thermal stress relief groove of the aero-engine turbine guide as described in any one of claims 1-8 includes the following steps: S1, fixing the turbine guide on the positioning member, then rotating the positioning member relative to the support member to align the positioning hole (210) with the fixing hole, and finally inserting the fixing pin into the positioning hole (210) and the fixing hole; S2, clamping the contour electrode (300) with the clamping member, straightening the contour electrode (300), and then connecting it to the machining machine tool with the connecting member; S3, aligning the contour electrode (300) and moving the contour electrode (300) to the position to be machined. At the working position, the thermal stress relief groove corresponding to the positioning hole (210) is processed until the thermal stress relief groove is formed; S4, the fixing pin is pulled out, and then the positioning member is rotated relative to the support member so that the next positioning hole (210) is aligned with the fixing hole, and then the fixing pin is inserted into the positioning hole (210) and the fixing hole. Finally, the contour electrode (300) is moved to the processing position to process the thermal stress relief groove corresponding to the positioning hole (210) until the thermal stress relief groove is formed; S5, step S4 is repeated until all the thermal stress relief grooves to be processed are formed.

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