Ceramic matrix composite high-pressure turbine guide vane assembly tool and assembly method

Abstract

The application relates to a high-pressure turbine guide vane assembling tool, in particular to a ceramic matrix composite high-pressure turbine guide vane assembling tool and assembling method. The application solves the technical problems of low assembling precision and high processing difficulty of the existing ceramic matrix composite high-pressure turbine guide vane assembling tool and assembling method. The ceramic matrix composite high-pressure turbine guide vane assembling tool comprises a base, a lower edge plate support, a blade body support assembly and an upper edge plate support. The base is provided with a longitudinal groove and two transverse grooves; the longitudinal groove is used for fixing the blade body support assembly; the two transverse grooves are respectively used for fixing the lower edge plate support and the upper edge plate support; the lower edge plate support comprises a left side plate and a plurality of lower edge plate profile detection bosses; the blade body support assembly comprises a front support block and a rear support block; and the upper edge plate support comprises a right side plate and a plurality of upper profile detection bosses. The application further provides a ceramic matrix composite high-pressure turbine guide vane assembling method.

Description

Technical Field

[0001] This invention relates to an assembly tooling for a high-pressure turbine guide vane, specifically to an assembly tooling and assembly method for a ceramic matrix composite high-pressure turbine guide vane. Background Technology

[0002] In the turbine engine structure of aero engines, the turbine system is the system with the largest thermal and power load. It is characterized by high output power, high operating temperature, light weight requirements, and small structural size. The guide vanes at the turbine inlet are the components with the highest operating temperature in the turbine system.

[0003] Ceramic matrix composites possess advantages such as low weight, high heat resistance, acid and corrosion resistance, and high strength and toughness. Furthermore, compared to high-temperature alloys, ceramic matrix composites exhibit higher stability and longer service life in high-temperature combustion gas environments, making them a preferred material for high-pressure turbine guide vanes.

[0004] The integral molding and weaving of ceramic matrix composite high-pressure turbine guide vanes is difficult, and the root strength of the blade is poor. Therefore, a disassembled structure is used to separately manufacture the blade body, upper edge plate, and lower edge plate, etc., and then the components are assembled into a high-pressure turbine guide vane. Compared with conventional products, the assembly of high-pressure turbine guide vanes involves more aspects, more complex assembly processes, and higher testing requirements.

[0005] Existing assembly methods typically employ a flange-based approach, installing and fixing the flange assembly on one side of the blade. The blade and the other flange are then positioned and installed sequentially using the flange as a reference, and finally secured as a whole using assembly fixtures. As a critical component of the high-pressure turbine guide vane assembly, the blade requires high installation precision. However, the aforementioned assembly method is prone to blade misalignment due to flange installation errors, resulting in poor final product quality that fails to meet usage requirements. Furthermore, during the assembly process using fixtures, the flange portions on both sides are obstructed, hindering the machining and inspection of the flange assembly. Summary of the Invention

[0006] The purpose of this invention is to address the technical problems of low assembly accuracy leading to poor product quality and high processing difficulty in existing assembly tooling and methods for ceramic matrix composite high-pressure turbine guide vanes. This invention provides an assembly tooling and method for ceramic matrix composite high-pressure turbine guide vanes. The assembly tooling and method of this invention uses the blade body as the installation reference to install the fin plate assembly, which ensures the precise assembly of the ceramic matrix composite high-pressure turbine guide vane and guarantees the final product quality.

[0007] The technical solution of this invention is:

[0008] A ceramic-based composite high-pressure turbine guide vane assembly tooling, characterized by the following features:

[0009] Includes base, lower edge plate support, blade support assembly and upper edge plate support;

[0010] The base is provided with a longitudinal groove and two transverse grooves located on both sides of the longitudinal groove; the longitudinal groove is used to fix the blade support assembly; the two transverse grooves are used to fix the lower edge plate support and the upper edge plate support respectively.

[0011] The lower edge plate support includes a left side plate and multiple lower edge plate profile detection bosses located on the right side of the left side plate; the multiple lower edge plate profile detection bosses match and contact the outer surface of the lower edge plate of the ceramic matrix composite high-pressure turbine guide vane to be processed;

[0012] The blade support assembly includes a front support block and a rear support block; the upper rear side of the front support block is a concave curved surface; the upper front side of the rear support block is a convex curved surface; the convex and concave curved surfaces are in contact with the blade.

[0013] The upper edge plate support includes a right side plate and multiple upper surface detection bosses located on the left side of the right side plate; the multiple upper surface detection bosses match and contact the outer surface of the upper edge plate of the ceramic matrix composite high-pressure turbine guide vane to be processed.

[0014] Furthermore, windows are respectively provided in the middle part of the left and right side panels.

[0015] Furthermore, the lower edge plate support also includes a left support plate; the lower end of the left support plate is fixedly connected to the base, and the upper end is fixedly connected to the bottom of the left side plate; the upper edge plate support also includes a right support plate; the lower end of the right support plate is fixedly connected to the base, and the upper end is fixedly connected to the bottom of the right side plate.

[0016] Furthermore, the lower ends of the left support plate, the front support block, the rear support block, and the right support plate are each provided with an outer edge structure, and the lower edge plate support, the front support block, the rear support block, and the upper edge plate support are respectively fixedly connected to the base through their respective outer edge structures.

[0017] Furthermore, through grooves are provided on the concave and convex curved surfaces respectively.

[0018] Meanwhile, the present invention also provides a method for assembling ceramic matrix composite high-pressure turbine guide vanes, which is characterized by including the following steps:

[0019] Step 1) Prepare the blade body, upper edge plate assembly, and lower edge plate assembly using ceramic matrix composites; wherein: at least three left protrusions are provided on the left side of the blade body, with one left protrusion at the top and one at the bottom each having a through left mounting hole; at least three right protrusions are provided on the upper and lower parts of the right end of the blade body, with two right protrusions at the top and two at the bottom each having a through right mounting hole; the upper edge plate assembly includes a first upper edge plate limiting baffle, a second upper edge plate limiting baffle, a second upper edge plate, and a first upper edge plate; the second upper edge plate and the first upper edge plate are spliced ​​together to form the upper edge plate. The plate is provided with right window grilles that are adapted to the right boss; the left side of the upper edge plate is provided with a first upper groove and a first lower groove; the first upper edge plate limiting baffle and the second upper edge plate limiting baffle are respectively provided with right mounting bosses; the lower edge plate assembly includes a first lower edge plate limiting block, a second lower edge plate limiting block and a lower edge plate; the lower edge plate is provided with left window grilles that are adapted to the left boss; the right side of the lower edge plate is provided with a second upper groove and a second lower groove; the first lower edge plate limiting block and the second lower edge plate limiting block are respectively provided with left mounting bosses;

[0020] Step 2) Machining the pins and pin holes;

[0021] Step 3) Assemble the high-pressure turbine guide vanes

[0022] Step 3.1) Insert the right mounting bosses at both ends of the first upper edge plate limiting baffle into the two right mounting holes on the upper part of the blade body respectively; insert the right mounting bosses at both ends of the second upper edge plate limiting baffle into the two right mounting holes on the lower part of the blade body respectively;

[0023] Insert the right protrusions into the corresponding right window grilles, so that the first upper edge plate limiting baffle is embedded in the first upper groove on the upper left side of the second upper edge plate and the first upper edge plate and is flush with the left side, with an installation gap of ≤0.05mm;

[0024] Insert the right protrusions into the corresponding right window grilles respectively; so that the second upper edge plate limiting baffle is embedded in the first lower groove on the lower left side of the second upper edge plate and the first upper edge plate and is flush with the left side, with an installation gap ≤0.05mm;

[0025] Step 3.2) Insert the left mounting boss of the second lower edge plate limiting block into the left mounting hole on the upper part of the blade body; insert the left mounting boss of the first lower edge plate limiting block into the left mounting hole on the lower part of the blade body;

[0026] Insert the left protrusions into the corresponding left window grilles respectively; so that the second lower edge plate limiting block and the first lower edge plate limiting block are respectively embedded in the second upper groove and the second lower groove on the right side of the lower edge plate and are flush with the right side, with an installation gap ≤0.05mm;

[0027] Step 4) Using the ceramic-based composite high-pressure turbine guide vane assembly fixture described above, position the blade body using the blade support assembly, ensuring that the contact gap between the blade body profile and the support assembly profile is ≤0.05mm; using the blade body as a reference, adjust the positional relationship between the components in the lower edge plate assembly and the upper edge plate assembly until multiple lower profile detection bosses match and contact the outer surface of the lower edge plate; multiple upper profile detection bosses match and contact the outer surface of the upper edge plate, with a contact gap ≤0.05mm;

[0028] Step 5) Insert pins and use them to fix the lower edge plate assembly and the upper edge plate assembly respectively, thus completing the assembly of the ceramic matrix composite high-pressure turbine guide vane.

[0029] Furthermore, in step 4), after multiple lower profile detection bosses match and contact the outer surface of the lower edge plate, the gap between the profiles is then detected online to ensure that the lower edge plate is installed in place.

[0030] In step 4), after multiple upper surface detection bosses match and contact the outer side of the upper edge plate, the gap between the surfaces is then detected online to ensure that the upper edge plate assembly meets the installation accuracy requirements.

[0031] Further, in step 4), the online inspection method is as follows: temporarily disassemble the upper edge plate support and the lower edge plate support, and use a coordinate measuring machine to conduct a comprehensive inspection of the overall surface and external dimensions of the product.

[0032] The beneficial effects of this invention are:

[0033] 1. The present invention relates to a ceramic matrix composite high-pressure turbine guide vane assembly fixture and assembly method. The upper and lower edge plates are installed using the blade body as the installation reference. Compared with the traditional installation method using the edge plate as the reference, this method can solve the problems of large blade body installation errors and low assembly accuracy caused by assembling the blade body using the edge plate as the reference. At the same time, installing the upper and lower edge plates using the blade body as the installation reference provides sufficient operating space for installation, improves operability during installation, ensures proper installation of each component, improves assembly accuracy, and greatly reduces installation and processing difficulty, thus ensuring the final product quality of the high-pressure turbine guide vane.

[0034] 2. The ceramic-based composite high-pressure turbine guide vane assembly fixture of the present invention can detect the dimensions and surface accuracy of key assembly parts in the high-pressure turbine guide vane assembly by setting surface detection bosses on the sides of the lower edge plate support and the upper edge plate support, thereby improving the overall assembly accuracy of the assembly.

[0035] 3. The ceramic-based composite high-pressure turbine guide vane assembly tooling of the present invention can be used as a testing tooling after the processing and preparation of high-pressure turbine blade assemblies. When in use, the lower edge plate support and the upper edge plate support can be removed, and the key dimensions and surface accuracy of the upper and lower edge plates can be tested by high-precision measuring instruments to ensure the installation accuracy of the overall product.

[0036] 4. The ceramic-based composite high-pressure turbine guide vane assembly fixture of the present invention has windows in the middle of the left and right side plates, which can facilitate observation of whether the surface inspection boss is in contact with the upper and lower edge plates, ensuring proper installation.

[0037] 5. The ceramic-based composite high-pressure turbine guide vane assembly tooling of the present invention has weight-reducing grooves on the convex curved surface of the front support block and the concave curved surface of the rear support block, which reduces the overall weight of the tooling and minimizes the contact area between the tooling and the high-pressure turbine guide vane.

[0038] 6. The ceramic matrix composite high-pressure turbine guide vane assembly tooling of the present invention has a simple structure, convenient installation and reasonable design, which greatly improves the assembly accuracy of the high-pressure turbine guide vane.

[0039] 7. The assembly method of the ceramic matrix composite high-pressure turbine guide vane of the present invention involves temporarily fixing the high-pressure turbine blade assembly after overall installation, using process equipment for online testing, removing the lower edge plate support and the upper edge plate support, and conducting online testing on the surface installation accuracy of the upper and lower edge plates to ensure the installation accuracy of the overall assembly and the reliability of subsequent processing and manufacturing processes.

[0040] 8. The assembly method of the ceramic matrix composite high-pressure turbine guide vane of the present invention uses the assembly tooling of the present invention to assemble the high-pressure turbine guide vane, which facilitates the overall machining of the outer contour after installation and improves the final dimensional accuracy of the high-pressure turbine guide vane. Attached Figure Description

[0041] Figure 1 This is a schematic diagram of the assembly tooling for the ceramic matrix composite high-pressure turbine guide vane and the assembly of the ceramic matrix composite high-pressure turbine guide vane of the present invention.

[0042] Figure 2 yes Figure 1 Exploded view;

[0043] Figure 3 This is a schematic diagram of the structure of a ceramic matrix composite high-pressure turbine guide vane;

[0044] Figure 4 This is a schematic diagram of the blade structure of a ceramic matrix composite high-pressure turbine guide vane;

[0045] Figure 5 This is an exploded view of the upper edge plate assembly of a ceramic matrix composite high-pressure turbine guide vane;

[0046] Figure 6 This is an exploded view of the lower edge plate assembly of a ceramic matrix composite high-pressure turbine guide vane;

[0047] Figure 7 This is a schematic diagram of the installation of the upper edge plate assembly in the assembly method of the ceramic matrix composite high-pressure turbine guide vane of the present invention;

[0048] Figure 8 This is a schematic diagram of the lower edge plate assembly installation in the assembly method of the ceramic matrix composite high-pressure turbine guide vane of the present invention;

[0049] Figure 9 This is a schematic diagram of the rear support block structure of the ceramic matrix composite high-pressure turbine guide vane assembly tooling of the present invention;

[0050] Figure 10 This is a schematic diagram of the front support block structure of the ceramic matrix composite high-pressure turbine guide vane assembly tooling of the present invention;

[0051] Figure 11 This is a schematic diagram of the lower edge plate support structure of the ceramic matrix composite high-pressure turbine guide vane assembly tooling of the present invention;

[0052] Figure 12 This is a schematic diagram of the upper edge plate support structure of the ceramic matrix composite high-pressure turbine guide vane assembly tooling of the present invention.

[0053] Figure label:

[0054] 1-Blade body, 11-Left boss, 111-Left mounting hole, 12-Right boss, 121-Right mounting hole; 2-Lower edge plate assembly, 21-First lower edge plate limiting block, 22-Second lower edge plate limiting block, 23-Lower edge plate, 24-Left window grille, 25-Second upper groove, 26-Second lower groove, 27-Left mounting boss; 3-Upper edge plate assembly, 31-First upper edge plate limiting baffle, 32-Second upper edge plate limiting baffle, 33-Second upper edge plate, 34-First upper edge plate, 35-Right window grille, 36-First upper groove, 37-First lower groove, 38-Right mounting boss;

[0055] 4-Base, 5-Lower edge plate support, 51-Left side plate, 511-Lower profile inspection boss, 52-Left side support plate, 6-Blade support assembly, 61-Rear support block, 62-Front support block, 7-Upper edge plate support, 71-Right side plate, 711-Upper profile inspection boss, 72-Right side support plate, 9-Outer edge structure. Detailed Implementation

[0056] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0057] The present invention relates to a ceramic matrix composite high-pressure turbine guide vane assembly tooling, comprising a base 4, a lower edge plate support 5, a blade support assembly 6, and an upper edge plate support 7.

[0058] The base 4 is provided with a longitudinal groove and two transverse grooves located on both sides of the longitudinal groove, as well as threaded holes, pin holes, and inspection reference holes. The longitudinal groove is used to fix 6; the two transverse grooves fix the lower edge plate support 5 and the upper edge plate support 7, respectively.

[0059] The lower edge plate support 5 includes a left side plate 51, a left side support plate 52, and multiple lower profile detection bosses 511 disposed on the right side of the left side plate 51. The multiple lower profile detection bosses 511 match and contact the outer surface of the lower edge plate 23 of the ceramic matrix composite high-pressure turbine guide vane to be processed. The lower end of the left side support plate 52 is fixedly connected to the base 4, and the upper end is fixedly connected to the bottom of the left side plate 51. In this example, the upper end of the left side plate 51 is provided with a platform protrusion extending to the right, so that the bottom surface of the boss of the lower edge plate 23 is in close contact with the platform protrusion of the left side plate 51. Windows are provided in the middle section of the left side plate 51 to facilitate observation during assembly to see whether the multiple lower profile detection bosses 511 are in contact with the outer surface of the lower edge plate 23, and to observe whether the assembly gap is too large, so as to make timely adjustments.

[0060] The blade support assembly 6 includes a front support block 62 and a rear support block 61. The upper rear side of the front support block 62 is a concave curved surface; the upper front side of the rear support block 61 is a convex curved surface; the convex and concave curved surfaces fit against the blade 1. The rear support block 61 is fixed in position, and the connecting pin holes and screw holes of the front support block 62 are set as oblong holes. During assembly, the front support block 62 and the rear support block 61 are fastened with bolts and nuts, so that the convex and concave curved surfaces are joined together to form a groove. The angle of the groove is the same as the required installation angle of the blade 1. The blade 1 is installed in the groove, and the blade 1 is adjusted so that the blade 1 fits against the groove surface, ensuring that the fitting gap is ≤0.05mm. In addition, through grooves are provided on the concave and convex curved surfaces respectively. In this embodiment, they are set as a sawtooth structure, which can reduce the overall weight of the assembly fixture.

[0061] The upper edge plate support 7 includes a right side plate 71, a right side support plate 72, and multiple upper surface detection bosses 711 disposed on the left side of the right side plate 71. These upper surface detection bosses 711 match and contact the outer surface of the upper edge plate of the ceramic matrix composite high-pressure turbine guide vane to be processed. The lower end of the right side support plate 72 is fixedly connected to the base 4, and the upper end is fixedly connected to the bottom of the right side plate 71. The upper surface of the upper edge plate support 7 is in close contact with the bottom surface of the bosses on the outer side of the first upper edge plate 34. Windows are provided in the middle section of the right side plate 71 to facilitate observation during assembly to determine whether the multiple upper surface detection bosses 711 are in contact with the outer surface of the upper edge plate, and to check whether the assembly gap is too large, allowing for timely adjustments.

[0062] For ease of installation, an outer edge structure 9 is provided at the lower end of the left support plate 52, the front support block 62, the rear support block 61, and the right support plate 72. The lower edge plate support 5 and the upper edge plate support 7 are L-shaped as a whole. The lower ends of the left support plate 52 and the right support plate 72 are adapted to the corresponding transverse grooves. The lower ends of the front support block 62 and the rear support block 61 are adapted to the longitudinal grooves. The lower edge plate support 5, the front support block 62, the rear support block 61, and the upper edge plate support 7 are fixedly connected to the base 4 through their respective outer edge structures 9.

[0063] Meanwhile, the present invention also provides a method for assembling ceramic matrix composite high-pressure turbine guide vanes, comprising the following steps:

[0064] Step 1) Prepare the blade body 1, upper edge plate assembly 3 and lower edge plate assembly 2 of the high-pressure turbine guide vane using ceramic matrix composites.

[0065] The blade 3 has a twisted cross-section curved surface structure with a hollow interior. At least three left protrusions 11 are provided on the left side of the blade 1, with one left protrusion 11 at the top and one at the bottom, each with a through left mounting hole 111. At least three right protrusions 12 are provided on the upper and lower parts of the right end of the blade 1, with two right protrusions 12 at the top and two at the bottom, each with a through right mounting hole 121. The lower edge plate assembly 2 and the upper edge plate assembly 3 are respectively installed on the left and right sides of the blade 1.

[0066] The upper edge plate assembly 3 mainly consists of four parts, including a first upper edge plate limiting baffle 31, a second upper edge plate limiting baffle 32, a second upper edge plate 33, and a first upper edge plate 34. The upper outer surface of the first upper edge plate 34 has an outwardly extending boss. The second upper edge plate 33 and the first upper edge plate 34 are riveted and spliced ​​together using ceramic-based composite pins to form the upper edge plate. The overall surface of the upper edge plate is curved. Right window grilles 35, respectively adapted to the right boss 12, are provided on the upper edge plate. A first upper groove 36 and a first lower groove 37 are provided on the left side of the upper edge plate. Both the first upper edge plate limiting baffle 31 and the second upper edge plate limiting baffle 32 are arc-shaped flat plates, and each of the first upper edge plate limiting baffle 31 and the second upper edge plate limiting baffle 32 is provided with a right mounting boss 38. During assembly, the first upper edge plate limiting baffle 31 and the second upper edge plate limiting baffle 32 are respectively embedded into the first upper groove 36 and the first lower groove 37 and are in close contact with the bottom of the groove, so that the right side of the first upper edge plate limiting baffle 31 and the second upper edge plate limiting baffle 32 are flush with the left side of the upper edge plate.

[0067] The lower edge plate assembly 2 is divided into three parts: a first lower edge plate limiting block 21, a second lower edge plate limiting block 22, and a lower edge plate 23. The lower edge plate 23 has a curved surface, and an outwardly extending boss is provided at the upper end of its outer side surface. The lower edge plate 23 is provided with left window grilles 24 that are adapted to the left boss 11; the right side of the lower edge plate 23 is provided with a second upper groove 25 and a second lower groove 26. The first lower edge plate limiting block 21 and the second lower edge plate limiting block 22 are arc plates with curved surfaces, and a left mounting boss 27 is provided on the first lower edge plate limiting block 21 and the second lower edge plate limiting block 22, respectively. During assembly, the first lower edge plate limiting block 21 and the second lower edge plate limiting block 22 are respectively embedded into the second upper groove 25 and the second lower groove 26 and made to fit in contact with the bottom of the groove, so that the left side of the first lower edge plate limiting block 21 and the second lower edge plate limiting block 22 are flush with the right side of the lower edge plate 23. The first lower edge plate limiting block 21 and the second lower edge plate limiting block 22 are respectively riveted and fixed to the lower edge plate 23 by composite pins.

[0068] Step 2) Machining the pins and pin holes;

[0069] Step 3) Assemble the high-pressure turbine guide vanes

[0070] Step 3.1) Insert the right mounting bosses 38 at both ends of the first upper edge plate limiting baffle 31 into the two right mounting holes 121 on the upper part of the blade body 1 respectively; insert the right mounting bosses 38 at both ends of the second upper edge plate limiting baffle 32 into the two right mounting holes 121 on the lower part of the blade body 1 respectively.

[0071] Insert the right protrusion 12 into the corresponding right window grille 35, so that the first upper edge plate limiting baffle 31 is embedded in the first upper groove 36 on the upper left side of the second upper edge plate 33 and the first upper edge plate 34 and is flush with the left side, with an installation gap ≤0.05mm.

[0072] Insert the right protrusion 12 into the corresponding right window grille 35 respectively; so that the second upper edge plate limiting baffle 32 is embedded in the first lower groove 37 on the lower left side of the second upper edge plate 33 and the first upper edge plate 34 and is flush with the left side, with an installation gap ≤0.05mm;

[0073] Step 3.2) Insert the left mounting boss 27 of the second lower edge plate limiting block 22 into the left mounting hole 111 on the upper part of the blade body 1; insert the left mounting boss 27 of the first lower edge plate limiting block 21 into the left mounting hole 111 on the lower part of the blade body 1;

[0074] Insert the left protrusion 11 into the corresponding left window grille 24 respectively; so that the second lower edge plate limiting block 22 and the first lower edge plate limiting block 21 are respectively embedded in the second upper groove 25 and the second lower groove 26 on the right side of the lower edge plate 23 and are flush with the right side, with an installation gap ≤0.05mm;

[0075] Step 4) Using the assembly fixture described above, position the blade 1 using the blade support assembly 6, temporarily support the blade 1 using the rear support block 61, and then clamp and fix the blade 1 using the front support block 62, ensuring that the contact gap between the blade 1 profile and the support assembly 6 profile is ≤0.05mm; using the blade 1 as a reference, adjust the positional relationship between the components in the lower edge plate assembly 2 and the upper edge plate assembly 3, so that the platform protrusion of the lower edge plate support 5 is in close contact with the boss on the outer side of the lower edge plate 23, and multiple lower profiles are inspected. The measuring boss 511 matches and is in close contact with the outer surface of the lower edge plate 23. By online detection of the surface gap, the fitting gap is ≤0.05mm, ensuring that the lower edge plate 23 is installed in place. The upper end face of the upper edge plate support 7 is in close contact with the bottom surface of the boss on the outer side of the first upper edge plate 34, and multiple upper surface measuring bosses 711 match and are in close contact with the outer surface of the upper edge plate. The fitting gap is ≤0.05mm. By online detection of the surface gap, it is ensured that the upper edge plate assembly 3 meets the installation accuracy requirements.

[0076] Step 5) Insert pins and use pins to fix the lower edge plate assembly 2 and the upper edge plate assembly 3 respectively, thus completing the processing of ceramic matrix composite high-pressure turbine guide vanes.

[0077] Using this assembly fixture as a machining fixture to clamp and fix the high-pressure turbine blades allows the machining datum of the high-pressure turbine guide vanes to be transferred to the assembly fixture. The overall shape of the high-pressure turbine blades can then be machined using CNC machining, ensuring the accuracy of the overall dimensions of the product.

[0078] During assembly, multiple upper and lower surface inspection bosses 711 and 511 on the inner sides of the upper and lower edge plate supports 7 and 5 can inspect the outer surfaces of the upper edge plate assembly 3 and the lower edge plate assembly 2. By online inspection of the installation gap between the inspection bosses and the upper and lower edge plate surfaces, the installation gap between the inspection bosses and the upper and lower edge plates is ensured to be ≤0.05mm, thereby ensuring the positional installation accuracy of the upper edge plate assembly 3 and the lower edge plate assembly 2. After the high-pressure turbine blade product is assembled, online inspection is performed. During online inspection, the upper and lower edge plate supports 7 and 5 can be temporarily disassembled, and a coordinate measuring machine can be used to comprehensively inspect the overall surface and external dimensions of the product. The assembly fixture not only has assembly functions but also online inspection functions. That is, after the final processing and preparation of the product, this assembly fixture can be used as an inspection fixture to perform final inspection of the overall surface and external dimensions of the assembly, ensuring the surface and dimensional accuracy requirements of the product.

Claims

1. A ceramic-based composite high-pressure turbine guide vane assembly tooling, characterized in that: It includes a base (4), a lower edge plate support (5), a blade support assembly (6), and an upper edge plate support (7); The base (4) is provided with a longitudinal groove and two transverse grooves located on both sides of the longitudinal groove; the longitudinal groove is used to fix the blade support assembly (6); the two transverse grooves fix the lower edge plate support (5) and the upper edge plate support (7) respectively; The lower edge plate support (5) includes a left side plate (51) and multiple lower edge plate profile detection bosses (511) disposed on the right side of the left side plate (51); the multiple lower profile detection bosses (511) match and contact the outer side of the lower edge plate (23) of the ceramic matrix composite high pressure turbine guide vane to be processed; The blade support assembly (6) includes a front support block (62) and a rear support block (61); the upper rear side of the front support block (62) is a concave curved surface; the upper front side of the rear support block (61) is a convex curved surface; the convex and concave curved surfaces are in contact with the blade. The upper edge plate support (7) includes a right side plate (71) and multiple upper surface detection bosses (711) disposed on the left side of the right side plate (71); the multiple upper surface detection bosses (711) match and contact the outer surface of the upper edge plate of the ceramic matrix composite high pressure turbine guide blade to be processed.

2. The ceramic matrix composite high-pressure turbine guide vane assembly tooling according to claim 1, characterized in that: The left side panel (51) and the right side panel (71) are respectively provided with windows in the middle part.

3. The ceramic matrix composite high-pressure turbine guide vane assembly tooling according to claim 1 or 2, characterized in that: The lower edge plate support (5) also includes a left side support plate (52); The lower end of the left support plate (52) is fixedly connected to the base (4), and the upper end is fixedly connected to the bottom of the left plate (51); The upper edge plate support (7) also includes a right side support plate (72); The lower end of the right support plate (72) is fixedly connected to the base (4), and the upper end is fixedly connected to the bottom of the right plate (71).

4. The ceramic matrix composite high-pressure turbine guide vane assembly tooling according to claim 3, characterized in that: The lower ends of the left support plate (52), the front support block (62), the rear support block (61) and the right support plate (72) are each provided with an outer edge structure (9). The lower edge plate support (5), the front support block (62), the rear support block (61) and the upper edge plate support (7) are fixedly connected to the base (4) through their respective outer edge structures (9).

5. The ceramic matrix composite high-pressure turbine guide vane assembly tooling according to claim 4, characterized in that: Through grooves are provided on the concave and convex curved surfaces respectively.

6. A method for assembling ceramic matrix composite high-pressure turbine guide vanes, characterized in that, Includes the following steps: Step 1) Prepare the blade (1), upper edge plate assembly (3), and lower edge plate assembly (2) using ceramic matrix composites respectively; wherein: at least three left protrusions (11) are provided on the left side of the blade (1), and one left protrusion (11) at the upper part and one at the lower part are provided with a through left mounting hole (111); at least three right protrusions (12) are provided on the upper and lower parts of the right end of the blade (1), and two right protrusions (12) at the upper and two at the lower part are provided with through right mounting holes (121); the upper edge plate assembly (3) includes a first upper edge plate limiting baffle (31), a second upper edge plate limiting baffle (32), a second upper edge plate (33), and a first upper edge plate (34); the second upper edge plate (33) and the first upper edge plate (34) are spliced ​​together to form an upper edge plate, and the upper edge plate is provided with The upper edge plate has a right window grille (35) that is adapted to the right boss (12); the left side of the upper edge plate is provided with a first upper groove (36) and a first lower groove (37); the first upper edge plate limiting baffle (31) and the second upper edge plate limiting baffle (32) are respectively provided with a right mounting boss (38); the lower edge plate assembly (2) includes a first lower edge plate limiting block (21), a second lower edge plate limiting block (22) and a lower edge plate (23); the lower edge plate (23) is provided with a left window grille (24) that is adapted to the left boss (11); the right side of the lower edge plate (23) is provided with a second upper groove (25) and a second lower groove (26); the first lower edge plate limiting block (21) and the second lower edge plate limiting block (22) are respectively provided with a left mounting boss (27); Step 2) Machining the pins and pin holes; Step 3) Assemble the high-pressure turbine guide vanes; Step 3.1) Insert the right mounting bosses (38) at both ends of the first upper edge plate limiting baffle (31) into the two right mounting holes (121) on the upper part of the blade (1); insert the right mounting bosses (38) at both ends of the second upper edge plate limiting baffle (32) into the two right mounting holes (121) on the lower part of the blade (1); Insert the right protrusion (12) into the corresponding right window grille (35) so that the first upper edge plate limiting baffle (31) is embedded in the first upper groove (36) on the upper left side of the second upper edge plate (33) and the first upper edge plate (34) and is flush with the left side, with an installation gap ≤0.05mm; Insert the right protrusion (12) into the corresponding right window grille (35); so that the second upper edge plate limiting baffle (32) is embedded in the first lower groove (37) on the lower left side of the second upper edge plate (33) and the first upper edge plate (34) and is flush with the left side, with an installation gap ≤0.05mm; Step 3.2) Insert the left mounting boss (27) of the second lower edge plate limiting block (22) into the left mounting hole (111) on the upper part of the blade (1); insert the left mounting boss (27) of the first lower edge plate limiting block (21) into the left mounting hole (111) on the lower part of the blade (1); Insert the left protrusion (12) into the corresponding left window grille (24); so that the second lower edge plate limiting block (22) and the first lower edge plate limiting block (21) are respectively embedded in the second upper groove (25) and the second lower groove (26) on the right side of the lower edge plate (23) and are flush with the right side, with an installation gap ≤0.05mm; Step 4) Using the ceramic matrix composite high-pressure turbine guide vane assembly fixture described in any of claims 1-5, position the blade (1) with the blade support assembly (6) and ensure that the fitting gap between the blade (1) profile and the support assembly (6) profile is ≤0.05mm; with the blade (1) as the reference, adjust the positional relationship between each component in the lower edge plate assembly (2) and the upper edge plate assembly (3) until multiple lower profile detection bosses (511) match and contact the outer side of the lower edge plate (23); multiple upper profile detection bosses (711) match and fit with the outer side of the upper edge plate, with a fitting gap ≤0.05mm; Step 5) Insert pins and use pins to fix the lower edge plate assembly (2) and the upper edge plate assembly (3) respectively, thus completing the processing of ceramic matrix composite high-pressure turbine guide vanes.

7. The method for assembling ceramic matrix composite high-pressure turbine guide vanes according to claim 6, characterized in that: In step 4), after multiple lower profile detection bosses (511) match and contact the outer side of the lower edge plate (23), the gap between the profiles is then detected online to ensure that the lower edge plate assembly (2) is installed in place. In step 4), after multiple upper surface detection bosses (711) match and contact the outer side of the upper edge plate, the gap between the surfaces is then detected online to ensure that the upper edge plate assembly (3) meets the installation accuracy requirements.

8. The method for assembling ceramic matrix composite high-pressure turbine guide vanes according to claim 7, characterized in that, In step 4), the online inspection method is as follows: temporarily disassemble the upper edge plate support (7) and the lower edge plate support (5), and use a coordinate measuring machine to conduct a comprehensive inspection of the overall surface and external dimensions of the product.

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