Metal framework ceramic-based variable geometry turbine guide blade

Abstract

The invention provides a metal framework ceramic-based variable geometry turbine guide vane, which belongs to the technical field of aero-engines, and 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 an air outlet communicated with the hollow structure is formed in the cylindrical side wall of the metal upper rotary table; 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; and the metal lower rotary table is installed on the turbine inner casing, a metal blade body section is fixedly connected to the metal lower rotary table, the metal blade body section penetrates through the hollow structure of the CMC blade body and extends into the metal upper rotary table, and a metal lower rotary table connecting section matched with the second groove is arranged on the upper portion of the metal lower rotary table.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aero-engines, and particularly relates to a metal framework ceramic matrix variable geometry turbine guide vane. BACKGROUND

[0002] In order to maximize the performance and efficiency of the variable cycle engine during the entire subsonic and supersonic flight, the rotating low-pressure turbine guide vane is usually used to adjust the gas flow by changing the throat area of the low-pressure turbine guide vane, so as to meet the needs of different engine working states. At present, in order to realize the rotation of the low-pressure turbine guide vane, the blade body is separated from the upper and lower edge plates, and rotating platforms are added at the upper and lower ends of the blade body to form a variable geometry low-pressure turbine guide vane. The angle between the blade and the main flow gas is adjusted by rotating the blade to change the throat area, so as to realize flow regulation.

[0003] In order to increase the engine thrust and improve the engine efficiency, on the one hand, the turbine inlet temperature needs to be increased, and on the other hand, the use of blade cold air (cold air is usually taken from the compressor, which will reduce the engine efficiency) needs to be reduced. Therefore, the ceramic matrix composite (CMC) blade emerges as the times require, aiming to withstand higher gas temperature with the least cold air (even without cold air), so as to realize the high efficiency of the engine.

[0004] However, the turbine guide vane in the prior art is a full-metal blade and is cooled by air cooling, but it cannot withstand higher temperatures, and the CMC blade with high temperature resistance cannot withstand greater stress.

[0005] Therefore, there is a need for a variable geometry turbine guide vane that can withstand higher and higher turbine inlet temperatures and has a relatively strong stress level. SUMMARY

[0006] The purpose of the present application is to provide a metal framework ceramic matrix variable geometry turbine guide vane to solve or alleviate at least one problem in the background art.

[0007] The technical solution of the present application is: a metal framework ceramic matrix variable geometry turbine guide vane, comprising:

[0008] A metal upper rotating platform is installed on the turbine outer casing, the inside of the metal upper rotating platform is a hollow structure, and the cylindrical side wall of the metal upper rotating platform is provided with an air inlet communicating with the hollow structure, and the lower side of the metal upper rotating platform is provided with a first groove;

[0009] A CMC blade body, which is internally hollow, and an upper side of the CMC blade body is provided with a CMC blade body connecting section adapted to the first groove, the CMC blade body connecting section is inserted into the first groove to realize the connection of the CMC blade body and the metal upper turntable, and a lower side of the CMC blade body is provided with a second groove; and

[0010] A metal lower turntable mounted on a turbine inner casing, the metal lower turntable is fixedly connected with a metal blade body section, the metal blade body section penetrates through the hollow structure of the CMC blade body and extends into the metal upper turntable, and an upper part of the metal lower turntable is provided with a metal lower turntable connecting section adapted to the second groove.

[0011] In at least one embodiment of the present application, the air inlet is multiple and circumferentially distributed.

[0012] In at least one embodiment of the present application, the first groove and the CMC blade body connecting section are of the same shape, and the size of the first groove is greater than that of the CMC blade body connecting section, so that a gap is formed between the first groove and the CMC blade body connecting section.

[0013] In at least one embodiment of the present application, an end of the CMC blade body connecting section is provided with a transversely extending boss, and the boss is clamped with the first groove.

[0014] In at least one embodiment of the present application, the second groove and the metal lower turntable connecting section are of the same shape, and the size of the second groove is greater than that of the metal lower turntable connecting section, so that a gap is formed between the second groove and the metal lower turntable connecting section.

[0015] The metal framework ceramic-based variable geometry turbine guide vane provided by the present application uses a metal framework as a bearing structure, uses metal to bear a larger load, avoids the disadvantage that CMC material cannot bear strong force, only plays the advantage of high temperature resistance, combines the respective advantages of metal and CMC, maximizes the functions of the two materials, so that the variable geometry flow regulation demand can be met at the same time, the least cold gas is used to bear a higher gas temperature, and high efficiency of the engine is realized. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical solutions provided by the present application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the present application.

[0017] Figure 1 A front view of the metal framework ceramic-based variable geometry turbine guide vane of the present application.

[0018] Figure 2A perspective view of a metal matrix ceramic variable geometry turbine vane according to the present application.

[0019] Figure 3 An axonometric view of a metal matrix ceramic variable geometry turbine vane according to the present application.

[0020] Figure 4 A schematic view of a metal upper turntable and CMC blade body connection structure according to the present application.

[0021] Figure 5 A schematic view of a metal lower turntable and CMC blade body connection structure according to the present application. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme of the present application will be described in more detail below with reference to the accompanying drawings of the present application.

[0023] The present application provides a structure of a metal matrix ceramic variable geometry turbine vane, which combines the variable geometry flow regulation function with the CMC blade, can meet the variable geometry flow regulation requirement, uses the least cooling gas (even no cooling gas) to withstand higher gas temperature, and maximizes the engine performance.

[0024] As shown in Figures 1 to 5 The metal matrix ceramic variable geometry turbine vane 100 provided by the present application includes a metal upper turntable 10, a metal lower turntable 20 and a CMC blade body 30.

[0025] The metal upper turntable 10 is the starting part of the variable geometry regulation, which is installed in the turbine outer casing and rotated by the regulating mechanism to drive the blade to rotate. The metal upper turntable 10 is a hollow structure, and one or more air inlets 11 are arranged on the side wall of the cylindrical turntable for introducing cooling gas. For example, in the illustrated embodiment of the present application, three rectangular air inlets 11 are arranged on the side wall of the cylindrical turntable of the metal upper turntable 10, and the three rectangular air inlets 11 are circumferentially distributed.

[0026] The CMC blade body 20 is integrally formed to realize the function of the guide vane. The CMC blade body 20 has the same or similar vane shape as the metal-based blade body to realize the guidance of the airflow, and the inside of the CMC blade body 20 is a hollow structure. The upper end of the CMC blade body 20 is provided with a CMC blade body connecting section 31, and the end of the CMC blade body connecting section 31 is provided with a transversely extending boss 32. The lower end of the metal upper turntable 10 is provided with a first groove 12 matched with the CMC blade body connecting section 31. The first groove 12 can be rectangular, strip-shaped or elliptical, etc. The CMC blade body connecting section 31 is inserted into the first groove 12 at the lower end of the metal upper turntable 10, and the boss 32 and the first groove 12 are clamped to form a mortise and tenon structure, thereby realizing the assembly and fixation of the CMC blade body 20 and the metal upper turntable 10. The shape of the first groove 12 is the same as that of the CMC blade body connecting section 31, but the size of the first groove 12 is slightly larger than that of the CMC blade body connecting section 31, so that a gap is left between the two to prevent the CMC blade body 20 from being clamped in the first groove 12 of the metal upper turntable 10, thereby causing a large stress concentration and leading to the damage of the blade body.

[0027] The metal lower turntable 20 is installed in the corresponding position of the turbine inner casing and is an integral structure with the metal blade section 21. After assembly, the metal blade section 21 is finally connected with the metal upper turntable 10, thereby forming a complete metal skeleton. Cooling gas can flow from the metal upper turntable 10 to the metal blade section 21 and then to the metal lower turntable 20, thereby cooling itself.

[0028] The upper side of the metal lower turntable 20 is provided with a metal lower turntable connecting section 22, and the lower end of the CMC blade body 30 is also provided with a second groove 33 matched with the metal lower turntable connecting section 22. The second groove 33 can be rectangular, elliptical or strip-shaped, etc. The metal lower turntable connecting section 22 of the metal lower turntable 20 is inserted into the second groove 33, and the two form a mortise and tenon structure, thereby realizing the assembly and fixation of the CMC blade body 30 and the metal lower turntable 20. The shape of the second groove 33 is the same as that of the metal lower turntable connecting section 22, but the size of the second groove 33 is slightly larger than that of the metal lower turntable connecting section 22, so that a gap is left between the two to prevent the CMC blade body 30 from being clamped in the metal lower turntable 20, thereby causing a large stress concentration and leading to the damage of the blade body.

[0029] The metal skeleton drives the CMC blade body 30 to rotate through the metal lower turntable connecting section 22 and the CMC blade body connecting section 31, thereby realizing the variable geometry adjustment function.

[0030] The metal framework ceramic matrix variable geometry turbine guide vane provided in the application adopts a metal framework as a bearing structure, uses metal to bear a larger load, avoids the disadvantage that CMC material cannot bear strong force, only plays the advantage of high temperature resistance, combines the respective advantages of metal and CMC, maximally plays the functions of the two kinds of materials, so that the variable geometry flow regulation demand can be met, the least cold air (even no cold air) is used to bear a higher gas temperature, and high efficiency of the engine is realized.

[0031] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed in the application, which should be covered in the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A metal matrix ceramic variable geometry turbine guide vane, characterized by, The application relates to a metal upper turntable installed on a turbine outer casing, a CMC blade body and a metal lower turntable installed on a turbine inner casing. The metal upper turntable is internally hollow, and a gas inlet communicating with the hollow structure is arranged on the cylindrical side wall of the metal upper turntable; the lower side of the metal upper turntable is provided with a first groove; The CMC blade body is internally hollow, and the upper side of the CMC blade body is provided with a CMC blade body connecting section matching the first groove; the CMC blade body connecting section is inserted into the first groove to realize the connection between the CMC blade body and the metal upper turntable; the lower side of the CMC blade body is provided with a second groove; and The metal lower turntable is fixedly connected with a metal blade body section, the metal blade body section penetrates through the hollow structure of the CMC blade body and extends into the metal upper turntable, and the upper part of the metal lower turntable is provided with a metal lower turntable connecting section matching the second groove.

2. The metal matrix ceramic variable geometry turbine vane of claim 1, wherein, The gas inlets are multiple and are uniformly distributed in the circumferential direction.

3. The metal matrix ceramic variable geometry turbine vane of claim 1 wherein, The first groove and the CMC blade body connecting section are of the same shape, and the size of the first groove is larger than that of the CMC blade body connecting section, so that a gap is formed between the first groove and the CMC blade body connecting section.

4. The metal matrix ceramic variable geometry turbine vane of claim 3, wherein, The end of the CMC blade body connecting section is provided with a transversely extending boss which is clamped with the first groove.

5. The metal matrix ceramic variable geometry turbine vane of claim 1 wherein, The second groove and the metal lower turntable connecting section are of the same shape, and the size of the second groove is larger than that of the metal lower turntable connecting section, so that a gap is formed between the second groove and the metal lower turntable connecting section.

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