Ceramic matrix composite material turbine blade margin plate disc tenon connecting structure
By using a tenon-and-groove connection structure between ceramic matrix composite blades and metal turbine disk rim plates, the temperature resistance and weight issues of high-temperature alloy turbine blades are solved, resulting in reduced cooling air consumption and structural simplification, thereby improving engine performance and thrust-to-weight ratio.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-02-10
- Publication Date
- 2026-04-03
AI Technical Summary
Existing high-temperature alloy turbine blades have limited temperature resistance, high cooling requirements, complex structure, and high density, which leads to decreased engine performance and poor thrust-to-weight ratio. Furthermore, the forming process of ceramic matrix composite turbine blades is difficult and costly.
The blades are made of ceramic matrix composite material and the turbine disk is connected by a tenon joint on the rim plate. The blades adopt an airfoil-shaped rim plate and a dovetail tenon design. Combined with a three-dimensional woven integrated molding process, the blades and turbine disk are reliably connected, reducing the amount of cooling air used and the weight of the blades.
At the same temperature, the amount of cooling air used is reduced by 100%, the weight of the blades is reduced by 30% to 50%, the design and manufacturing costs are reduced, and the engine performance and thrust-to-weight ratio are improved.
Smart Images
Figure CN121781979A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aero-engine technology, and specifically relates to a ceramic matrix composite turbine blade edge plate tenon connection structure. Background Technology
[0002] With the continuous improvement of aero-engine performance, turbine inlet temperatures are constantly increasing. Engines with a thrust-to-weight ratio of 15-20 have turbine inlet temperatures reaching as high as 2300K, far exceeding the temperature resistance of even the most advanced high-temperature alloys. To address this issue, turbine blades require advanced cooling design and coating technologies to reduce surface temperatures. Previous turbine blade cooling design technologies primarily focused on high-pressure turbines. However, in recent years, with the rising turbine inlet temperatures, the cooling requirements for low-pressure turbine blades have become increasingly prominent, necessitating a greater volume of cooling air. Yet, to improve engine performance, the distribution of cooling air to hot-end components is reduced. This contradiction, besides requiring the development of more advanced cooling technologies, urgently necessitates the use of a new lightweight, high-temperature resistant material. This is both a necessity for improving engine performance and a key to increasing the engine's thrust-to-weight ratio.
[0003] Therefore, ceramic matrix composites (CMCs) have seen rapid development in recent years, driving their application in aero-engines. Among them, SiC / SiC composites, due to their high tensile strength, creep resistance, high temperature resistance, oxidation resistance, and good compatibility with ceramic matrices, have broad application prospects in aerospace, shipbuilding, and nuclear industries. Without air cooling and thermal barrier coatings, CMC materials can operate at temperatures 150°C to 350°C higher than nickel-based superalloys, with a potential operating temperature of up to 1650°C. Furthermore, their density is only 1 / 3 to 1 / 4 that of superalloys. Studies have shown that using CMC-SiC in hot-end components such as combustion chambers, turbines, afterburners, and nozzles can increase engine operating temperatures by 300°C to 500°C, reduce structural weight by 50% to 70%, increase thrust by 30% to 100%, and reduce cooling gas consumption by more than 30%. It is considered an ideal material for high-performance aero-engine hot-end components.
[0004] The application of CMC materials in aero-engines started relatively late, especially in rotor components, where it is still in the exploratory stage. Mainstream aero-engine low-pressure turbine blades still use nickel-based superalloys or single-crystal materials. Typical metallic low-pressure turbine blade structures include... Figure 1 and Figure 2As shown, the blade body 11 is formed by precision casting without any allowance, the tenon 12 is fir-shaped, the blade crown 13 is a serrated crown, and the internal structure is arranged with baffles, baffle columns and other structures for cooling and heat exchange. The blade surface is coated with a thermal barrier coating for heat insulation. In high-temperature areas, such as the leading edge and trailing edge areas, structures such as film cooling holes 14 and slotted exhaust windows 15 are arranged for cooling.
[0005] However, high-temperature alloys have limited temperature resistance, and the turbine blades require a large amount of cooling air, which reduces the engine's working capacity. In addition, the turbine blades made of high-temperature alloys have a complex structure, making structural design difficult. High-temperature alloys have a high density, resulting in heavy blades and large centrifugal loads, which is not conducive to improving the engine's thrust-to-weight ratio. Furthermore, the use of ceramic matrix composite materials to integrally mold the metal turbine blades is extremely difficult and has high manufacturing costs. Summary of the Invention
[0006] The purpose of this application is to provide a ceramic matrix composite turbine blade rim plate tenon connection structure to solve or alleviate at least one of the problems in the prior art.
[0007] The technical solution of this application is: a ceramic matrix composite turbine blade rim plate tenon connection structure, comprising:
[0008] A ceramic matrix composite blade, the blade having a crown and a tenon;
[0009] The rim plate adopts an "airfoil" rim plate structure. The rim plate has recesses on both sides of its circumference and semi-tenons on both sides of its front and rear ends. The recesses of two adjacent rim plates cooperate to form a through groove for the blade body to pass through. The semi-tenons of two adjacent rim plates cooperate to form a rim plate tenon. The rim plate tenon has the same shape as the blade tenon. The rim plate tenon and the blade tenon are inserted into the mortise of the turbine disk. The fixed connection with the turbine disk is achieved through the mortise and tenon structure of the rim plate and the blade.
[0010] In at least one embodiment of this application, the tenon is a straight single-tooth dovetail tenon.
[0011] In at least one embodiment of this application, the edging plate is made of a metallic material or a ceramic matrix composite material.
[0012] In at least one embodiment of this application, the leaf crown adopts a parallel crown structure and has at least two sealing grates arranged along the axial direction.
[0013] In at least one embodiment of this application, the blade crown, blade body, rootstock, and tenon are integrally formed into a preform by three-dimensional weaving of ceramic matrix composite material. The fibers of the ceramic matrix composite material are woven from the bottom of the tenon along the blade height direction, and the thickness of the preform is varied by changing the thickness of the weft yarn in areas with drastic thickness changes.
[0014] In at least one embodiment of this application, a “T”-shaped leaf crown base is formed by turning the fiber cloth of the blade tip pressure surface and the blade tip suction surface outward to both sides, and then the leaf crown thickness is increased by a lay-up process to form a leaf crown preform.
[0015] The CMC turbine blade edge plate tenon connection structure provided in this application, under the same temperature level, reduces the cooling gas consumption from 2.3% to 0% compared with turbine blades made of high-temperature alloy materials, resulting in a 100% reduction in cooling gas consumption and improved overall engine performance. At the same time, the density of ceramic matrix composite material is only 1 / 4 to 1 / 3 of that of high-temperature alloy materials, reducing blade weight by 30% to 50%, which can improve the engine thrust-to-weight ratio and minimize the turbine structure modifications caused by the application of ceramic matrix composite material, thus greatly reducing design and manufacturing costs. Attached Figure Description
[0016] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.
[0017] Figure 1 This is a front view of the working blade structure of a low-pressure turbine made of high-temperature alloy material.
[0018] Figure 2 This is a side view of the working blade structure of a low-pressure turbine made of high-temperature alloy material.
[0019] Figure 3 This is a schematic diagram of the tenon-and-groove connection structure of the ceramic matrix composite turbine blade rim plate of this application.
[0020] Figure 4 This is a schematic diagram of the ceramic matrix composite turbine blade of this application.
[0021] Figure 5 This is a schematic diagram of the rim plate of this application.
[0022] Figure 6 This is a schematic diagram of the blade prefabricated structure in this application.
[0023] Figure 7 This is a schematic diagram of the leaf crown prefabricated structure in this application. Detailed Implementation
[0024] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.
[0025] In order to improve the temperature resistance of turbine blades, reduce the amount of cooling air used in the engine, reduce the weight of the blades, improve the overall performance of the engine, reduce the difficulty of the forming process and manufacturing cost of ceramic matrix composite turbine blades, and improve the connection reliability between the turbine blades and the disk, this application provides a tenon-and-groove connection structure for the edge plate of a ceramic matrix composite (CMC) turbine blade.
[0026] like Figures 3-5 As shown, the CMC turbine blade rim plate tenon connection structure 20 provided in this application includes: a blade 21 made of CMC material and a rim plate 24. The blade 21 has a solid blade body, with a crown 22 at the radially outer tip and a tenon 23 at the radially inner root. The tenon 23 is a straight, single-tooth dovetail tenon, smoothly connected to the blade body via an extension root section. The crown, blade body, extension root, and tenon are integrated into a single structure, maximizing fiber continuity and improving the rotor blade's load-bearing capacity. The rim plate 24 adopts an airfoil-shaped rim plate structure. Recesses 241 are provided on both circumferential sides of the rim plate 24, and half-tenons 242 are provided on both sides of the front and rear end faces of the rim plate 24. The recesses 241 of two adjacent rim plates 24 cooperate to form a passageway through which the blade body of the blade 21 passes. The half-tenons 242 of two adjacent rim plates 24 cooperate to form a rim plate tenon, which has the same shape as the tenon 23 of the blade 21. The blade 21 is limited by the rim plate 24. The tenon of the rim plate 24 and the tenon 23 of the blade are inserted into the mortise 31 of the wheel disk 30, and a fixed connection with the turbine disk 30 is achieved through the mortise and tenon structure.
[0027] In the ceramic matrix composite (CMC) turbine blade edge plate tenon connection structure of this application, the ceramic matrix composite blade 21 and edge plate 24 are connected to the turbine disk 30 by dovetail tenons, which can realize a reliable connection between the CMC material blade and the metal material turbine disk.
[0028] In some embodiments of this application, the edging plate 24 may be made of metal material. For example, the edging plate 24 may be made of nickel-based or cobalt-based high-temperature alloy material, or it may be made of single-crystal high-temperature alloy material, or the edging plate 24 may be made of ceramic matrix composite material.
[0029] In some embodiments of this application, the leaf crown 22 adopts a parallel crown structure, with at least two sealing grates arranged axially front and back.
[0030] In this application, the ceramic matrix composite preform of the blade 21 is manufactured using a three-dimensional integrated weaving and lay-up molding process. To ensure blade strength and fiber integrity, the inner tenon, extension root, and blade preform of the ceramic matrix composite are integrally molded using a three-dimensional weaving process. The fibers are woven from the bottom of the tenon 23 along the blade height. For areas with significant thickness variations—such as the inner tenon—the thickness of the inner tenon preform is varied by changing the weft yarn thickness, aiming to simultaneously meet the requirements of varying thickness and yarn continuity. The structure of the inner tenon preform is as follows: Figure 6 As shown. Further, for the crown 22 of the CMC material blade 21, the fiber cloth on the pressure surface and suction surface of the blade tip is turned outwards to both sides to form a "T"-shaped structure of the crown base. Then, the crown thickness is increased through a lay-up process to form a crown preform, as shown. Figure 7 As shown.
[0031] The CMC turbine blade edge plate tenon connection structure provided in this application, under the same temperature level, reduces the amount of cold air consumption from 2.3% to 0% compared with turbine blades made of high-temperature alloy materials, resulting in a 100% reduction in cold air consumption and improved overall engine performance. At the same time, the density of ceramic matrix composite material is only 1 / 4 to 1 / 3 of that of high-temperature alloy materials, reducing the blade weight by 30% to 50% and improving the engine thrust-to-weight ratio.
[0032] The ceramic matrix composite turbine blades of this application can typically be used in low-pressure turbine working blades (rotor blades). They can achieve the connection between CMC blades and metal turbine disks, which can minimize the turbine structure changes caused by the application of ceramic matrix composites and greatly reduce design and manufacturing costs.
[0033] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A ceramic matrix composite turbine blade rim plate tenon joint structure, characterized in that, include: A ceramic matrix composite blade (21) having a crown (22) and a tenon (23); The rim plate (24) adopts an "airfoil" rim plate structure. The rim plate (24) has recesses (241) on both sides of its circumference and half tenons (242) on both sides of its front and rear ends. The recesses (241) of two adjacent rim plates (24) cooperate to form a through groove for the blade body part of the blade (21) to pass through. The half tenons (242) of two adjacent rim plates (24) cooperate to form a rim plate tenon. The rim plate tenon and the tenon (23) of the blade (21) have the same shape. The rim plate tenon and the tenon (23) of the blade (21) are inserted into the mortise (31) of the wheel disk (30). The fixed connection with the turbine disk (30) is achieved through the mortise and tenon structure of the rim plate (24) and the blade (21).
2. The ceramic matrix composite turbine blade rim plate tenon connection structure as described in claim 1, characterized in that, The tenon (23) is a straight single-tooth dovetail tenon.
3. The ceramic matrix composite turbine blade rim plate tenon connection structure as described in claim 1, characterized in that, The flange (24) is made of metal or ceramic matrix composite material.
4. The ceramic matrix composite turbine blade rim plate tenon connection structure as described in claim 1, characterized in that, The leaf crown (22) adopts a parallel crown structure and has at least two sealing teeth arranged along the axial direction.
5. The ceramic matrix composite turbine blade rim plate tenon connection structure as described in claim 1, characterized in that, The leaf crown (22), leaf body, root extension, and tenon (23) of the blade (21) are formed into a preform by three-dimensional weaving of ceramic matrix composite material. The fibers of the ceramic matrix composite material are woven from the bottom of the tenon (23) along the leaf height direction, and the thickness of the preform is varied by changing the thickness of the weft yarn in areas where the thickness changes drastically.
6. The ceramic matrix composite turbine blade rim plate tenon connection structure as described in claim 5, characterized in that, The fiber cloth on the blade tip pressure surface and the blade tip suction surface is turned outward to both sides to form a "T" shaped blade crown base. Then, the thickness of the blade crown is increased by the lay-up process to form a blade crown preform.