Detachable self-locking metal framework ceramic-based variable geometry turbine guide blade

Abstract

The invention provides a detachable self-locking metal framework ceramic-based variable geometry turbine guide vane, and belongs to the technical field of aero-engines, the detachable self-locking metal framework ceramic-based variable geometry turbine guide vane comprises a metal upper rotary table mounted on a turbine outer casing, the interior of the metal upper rotary table is of a hollow structure, an air inlet communicated with the hollow structure is formed in the cylindrical side wall of the metal upper rotary table, and a first groove is formed in the lower side of the metal upper rotary table; the interior of the CMC blade body is of a hollow structure, the upper side of the CMC blade body is provided with a CMC blade body connecting section matched with the first groove, the CMC blade body connecting section is inserted into the first groove so that the CMC blade body can be connected with the upper metal rotary table, and a second groove is formed in the lower side of the CMC blade body; a metal blade body section is fixedly connected to the metal lower rotary table, a metal lower rotary table connecting section matched with the second groove is arranged on the upper portion of the metal lower rotary table, a self-locking hook is arranged at the end of the metal blade body section, a mounting plate is arranged in the metal upper rotary table, and when the metal blade body section penetrates through the CMC blade body and extends into the metal upper rotary table, the metal blade body section is fixedly connected with the metal lower rotary table connecting section. And the self-locking hook is hooked on the mounting plate.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to a detachable, self-locking metal-framed ceramic-based variable geometry turbine guide vane. Background Technology

[0002] To maximize the performance and efficiency of variable cycle engines throughout subsonic and supersonic flight, the flow rate is typically adjusted by rotating low-pressure turbine guide vanes to change the throat area of ​​the low-pressure turbine guide vane, thus meeting the needs of different engine operating conditions. Currently, to achieve low-pressure turbine guide vane rotation, the blade body is separated from the upper and lower edge plates, and a rotating platform is added to both ends of the blade body to form a variable geometry low-pressure turbine guide vane. By rotating the blade, the angle between the blade and the mainstream gas flow is adjusted, thereby changing the throat area and achieving flow regulation.

[0003] To increase engine thrust and improve engine efficiency, it is necessary to increase the turbine inlet temperature and reduce the amount of cooling air used in the blades (cooling air usually enters from the compressor, which reduces engine efficiency). Therefore, ceramic matrix composite (CMC) blades have emerged, designed to withstand higher combustion gas temperatures with minimal (or even no) cooling air, thereby achieving higher engine efficiency.

[0004] However, existing turbine guide vanes are all-metal blades and are cooled by air, but they cannot withstand higher temperatures, while CMC blades, which are resistant to high temperatures, cannot withstand greater stress.

[0005] Therefore, a variable geometry turbine guide vane is needed that can withstand increasingly higher turbine inlet temperatures and has a high stress level. Summary of the Invention

[0006] The purpose of this application is to provide a metal-framed ceramic-based variable geometry turbine guide vane to solve or mitigate at least one of the problems in the prior art.

[0007] The technical solution of this application is: a metal-framed ceramic-based variable geometry turbine guide vane, comprising:

[0008] A metal upper turntable is installed on the outer casing of the turbine. The interior of the metal upper turntable is a hollow structure and an air inlet communicating with the hollow structure is provided on the cylindrical side wall of the metal upper turntable. A first groove is provided on the lower side of the metal upper turntable.

[0009] The CMC blade has a hollow internal structure, and its upper side has a CMC blade connecting section that fits into the first groove. The CMC blade connecting section is inserted into the first groove to connect the CMC blade to the metal upper turntable. The lower side of the CMC blade has a second groove.

[0010] A lower metal turntable is installed on the inner casing of the turbine. A metal blade section is fixedly connected to the lower metal turntable. The upper part of the lower metal turntable is provided with a metal lower turntable connecting section that matches the second groove. The end of the metal blade section is provided with a self-locking hook. A mounting plate is provided in the hollow structure of the upper metal turntable. When the metal blade section passes through the hollow structure of the CMC blade and extends into the upper metal turntable, the self-locking hook hooks onto the mounting plate, thereby realizing the fixed connection between the upper metal turntable and the lower metal turntable.

[0011] In at least one embodiment of this application, the air inlets are multiple and evenly distributed in the circumferential direction.

[0012] In at least one embodiment of this application, the first groove has the same shape as the CMC blade connecting section, and the size of the first groove is larger than the size of the CMC blade connecting section, thereby forming a gap between the first groove and the CMC blade connecting section.

[0013] In at least one embodiment of this application, the metal blade segment is an elastic structure.

[0014] In at least one embodiment of this application, the mounting plate is composed of multiple sector structures spliced ​​together, with gaps between adjacent sector structures.

[0015] The metal-framed ceramic-based variable geometry turbine guide vane provided in this application uses a metal frame as the load-bearing structure. By utilizing the metal to bear a large load, it avoids the disadvantage of CMC materials being unable to withstand strong forces, and only takes advantage of its high temperature resistance. It combines the advantages of metal and CMC to maximize the function of both materials. Thus, while meeting the requirements of variable geometry flow regulation, it uses the least amount of cold air to withstand higher combustion gas temperatures, achieving high engine efficiency. At the same time, it provides a self-locking structure, which is convenient for assembly and not easy to fall off. This self-locking structure can be disassembled and removed without damage using tools, and any part can be replaced when needed, reducing the cost of use. 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 1This is a front view of the metal-framed ceramic-based variable geometry turbine guide vane of this application.

[0018] Figure 2 This is a perspective view of the metal-framed ceramic-based variable geometry turbine guide vane of this application.

[0019] Figure 3 This is a schematic diagram of the connection structure between the metal upper turntable and the CMC blade in this application.

[0020] Figure 4 This is a schematic diagram of the connection structure between the metal lower turntable and the CMC blade in this application. Detailed Implementation

[0021] 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.

[0022] This application proposes a structural form of a metal-framed ceramic-based variable geometry turbine guide vane. This structure combines variable geometry flow regulation function with CMC blades, which can meet the requirements of variable geometry flow regulation while using minimal (or even no) cooling air to withstand higher combustion gas temperatures, thereby maximizing engine performance. At the same time, the solution adopts a self-locking structure, which facilitates the assembly of the turbine guide vane and prevents it from falling off. This self-locking structure can be disassembled and removed without damage using tools, and any part can be replaced when needed, reducing the cost of use.

[0023] like Figures 1 to 4 As shown, the detachable self-locking metal-framed ceramic variable geometry turbine guide vane 100 provided in this application includes: a metal upper turntable 10, a metal lower turntable 20, and a CMC blade body 30.

[0024] The upper metal turntable 10 is the initiator of the variable geometry adjustment. It is installed in the outer casing of the turbine and rotates through the adjustment mechanism, thereby driving the blades to rotate. The upper metal turntable 10 has a hollow internal structure, and its cylindrical turntable sidewall has one or more air inlets 11 that connect to its internal central structure for introducing cooling gas. For example, in the embodiment illustrated in this application, the cylindrical turntable sidewall of the upper metal turntable 10 has three rectangular air inlets 11, which are evenly distributed circumferentially.

[0025] The CMC blade 20 is integrally formed and functions as a guide vane. The CMC blade 20 has a blade shape identical or similar to the metal base blade to guide airflow. The interior of the CMC blade 20 is hollow, and a CMC blade connecting section 31 is located at the upper end of the CMC blade 20. A first groove 12 matching the CMC blade connecting section 31 is located at the lower end of the metal upper turntable 10. For example, the first groove 12 can be rectangular, elongated, or elliptical. The CMC blade connecting section 31 is inserted into the first groove 12 at the lower end of the metal upper turntable 10, allowing the CMC blade 30 and the metal upper turntable 10 to rotate together in the circumferential direction.

[0026] The lower metal turntable 20 has a connecting section 22 on its upper side. The lower end of the CMC blade 30 also has a second groove 32 that matches the connecting section 22. For example, the second groove 32 can be rectangular, elliptical, or elongated. The connecting section 22 of the lower metal turntable 20 is inserted into the second groove 32, allowing the CMC blade 30 and the lower metal turntable 20 to rotate together in the circumferential direction. The second groove 32 has the same shape as the connecting section 22, but its size is slightly larger, leaving a gap between them to prevent the CMC blade 30 from getting stuck in the lower metal turntable 20, which could cause stress concentration and blade damage.

[0027] The lower metal turntable 20 is installed in the corresponding position in the inner casing of the turbine. The upper side of the connecting section 22 of the lower metal turntable is the metal blade section 1. The metal blade section 21 and the lower metal turntable 20 are an integral structure. During assembly, the metal blade section 21 passes through the hollow structure inside the CMC blade 30. The metal blade section 21 is an elastic structure that can deform to a certain extent. The end of the metal blade section 21 is provided with a self-locking hook 23. The hollow structure of the upper metal turntable 10 is provided with a mounting plate 13. The mounting plate 13 can be spliced ​​together from multiple circumferentially distributed sector segments with gaps between adjacent segments, thereby providing a certain elastic deformation capability. A through hole is formed at the center of the mounting plate 13. During installation, the end of the metal blade section 21 is slightly compressed and deformed by the internal pressure of the CMC blade 30. When it reaches the mounting plate 13, the end of the metal blade section 21 undergoes a large contraction deformation under the pressure of the through hole, and then releases and springs back to its original shape after passing through the through hole. The self-locking hook 23 at the end of the metal blade section 21 hooks onto the mounting plate 13, ensuring that the upper metal turntable 10 and the lower metal turntable 20 are connected and fixed and do not fall off.

[0028] In this application, in order to ensure that the self-locking hook 23 can pass smoothly through the through hole between the mounting plates 13, the upper side of the self-locking hook 23 is provided with a smooth structure.

[0029] In this application, the self-locking structure can be disassembled and reassembled without damage using tools, allowing for the replacement of any part whenever needed, thus reducing the cost of use.

[0030] The metal-framed ceramic-based variable geometry turbine guide vane provided in this application uses a metal frame as the load-bearing structure. By utilizing the metal to bear a large load, it avoids the disadvantage of CMC materials being unable to withstand strong forces, and only takes advantage of its high temperature resistance. It combines the advantages of metal and CMC to maximize the function of both materials. Thus, while meeting the requirements of variable geometry flow regulation, it uses minimal (or even no) cooling air to withstand higher combustion gas temperatures, achieving high engine efficiency. At the same time, it provides a self-locking structure, which is convenient for assembly and not easy to fall off. This self-locking structure can be disassembled and removed without damage using tools, and any part can be replaced when needed, reducing the cost of use.

[0031] 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 metal-framed ceramic-based variable geometry turbine guide vane, characterized in that, include: A metal upper turntable is installed on the outer casing of the turbine. The interior of the metal upper turntable is a hollow structure and an air inlet communicating with the hollow structure is provided on the cylindrical side wall of the metal upper turntable. A first groove is provided on the lower side of the metal upper turntable. The CMC blade has a hollow internal structure, and its upper side has a CMC blade connecting section that fits into the first groove. The CMC blade connecting section is inserted into the first groove to connect the CMC blade to the metal upper turntable. The lower side of the CMC blade has a second groove. A lower metal turntable is installed on the inner casing of the turbine. A metal blade section is fixedly connected to the lower metal turntable. The upper part of the lower metal turntable is provided with a metal lower turntable connecting section that matches the second groove. The end of the metal blade section is provided with a self-locking hook. A mounting plate is provided in the hollow structure of the upper metal turntable. When the metal blade section passes through the hollow structure of the CMC blade and extends into the upper metal turntable, the self-locking hook hooks onto the mounting plate, thereby realizing the fixed connection between the upper metal turntable and the lower metal turntable.

2. The metal-framed ceramic-based variable geometry turbine guide vane as described in claim 1, characterized in that, The air inlets are multiple and evenly distributed in the circumferential direction.

3. The metal-framed ceramic-based variable geometry turbine guide vane as described in claim 1, characterized in that, The first groove has the same shape as the CMC blade connecting section, and the size of the first groove is larger than the size of the CMC blade connecting section, thereby creating a gap between the first groove and the CMC blade connecting section.

4. The metal-framed ceramic-based variable geometry turbine guide vane as described in claim 1, characterized in that, The metal blade section is an elastic structure.

5. The metal-framed ceramic-based variable geometry turbine guide vane as described in claim 1, characterized in that, The mounting plate is composed of multiple sector structures spliced ​​together, with gaps between adjacent sector structures.

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