Gas turbine engine, low turboshaft assembly and core engine assembly method

Abstract

The invention aims to provide a gas turbine engine, a low-turboshaft assembly and a core engine assembling method, the low-turboshaft assembly comprises a low-pressure turbine shaft and an air guide pipe, the air guide pipe is arranged on the periphery of the low-pressure turbine shaft in a sleeving mode and fixedly connected with the low-pressure turbine shaft, and a plurality of vent holes are formed in a pipe body of the air guide pipe. By means of the low-turboshaft assembly, the problems caused by assembling and disassembling of the air guide pipe can be reduced, and the assembling and disassembling period of an engine is shortened.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine engines, and in particular to a gas turbine engine and a low-turbine shaft component thereof. Background Art

[0002] In the field of aviation engines, high bypass ratio turbofan engines are used in most current commercial aircraft due to their good stability, safety and economy. After entering the engine, the airflow is initially compressed by the fan blades. The compressed gas is diverted by the diverter ring, most of which enters the outer bypass flow channel, and the remaining airflow enters the core engine part through the supercharger stage, and is compressed, burned, and works by the high-pressure rotor, and finally discharged from the engine. Because the high-pressure turbine is a high-temperature component, it is necessary to bleed air from the cold end component for cooling during actual operation. At the same time, in order to prevent oil leakage from the middle bearing cavity and the rear bearing cavity, it is also necessary to bleed compressed air from the cooling component for sealing. The function of the air duct is to separate the two sealed cooling airflows.

[0003] In the existing engine structure, the front end of the turbine air duct is overlapped on the center of a certain stage of the compressor, and the rear end is fixed to the turbine rotor. In order to avoid affecting the connection in the middle of the high-pressure rotor, the air duct must be placed in the front cavity in actual assembly, and then the tooling is used to pull it up and connect it to the turbine rotor for fastening after the rotor connector is tightened. The installation and disassembly process of the air duct is blind, and it is difficult to disassemble. Especially after the engine has completed a long period of testing, the air duct and the turbine rotor may have problems such as adhesion and thread biting, which requires a longer time to disassemble, increasing the assembly and disassembly cycle, and is also not conducive to the replacement of cold and hot end components.

[0004] How to reduce the problems caused by the assembly and disassembly of air ducts and shorten the engine assembly and disassembly cycle is an issue that needs to be urgently addressed. Summary of the invention

[0005] The object of the present invention is to provide a low-turbo shaft assembly, which can reduce the problems caused by the assembly and disassembly of the air duct and shorten the assembly and disassembly cycle of the engine.

[0006] A low-turbulence shaft assembly for achieving the above-mentioned purpose comprises:

[0007] low pressure turbine shaft; and

[0008] The air duct is sleeved on the outer periphery of the low-pressure turbine shaft and fixedly connected to the low-pressure turbine shaft. A plurality of vent holes are opened in the pipe body of the air duct.

[0009] In one or more embodiments, the air duct comprises an inner tube wall, an outer tube wall and a tube body surrounded by the inner tube wall and the outer tube wall, and the plurality of ventilation holes are arranged in the tube body in an annular distribution along the circumference of the tube body.

[0010] In one or more embodiments, the plurality of ventilation holes are uniformly opened in the tube body along the circumference of the tube body.

[0011] In one or more embodiments, sealing units are provided at both ends of the air duct, and the sealing units are protruded outward from the outer tube wall.

[0012] In one or more embodiments, the sealing unit is a comb tooth protruding outward from the outer tube wall along the radial direction of the air duct.

[0013] In one or more embodiments, the sealing unit is a brush seal that is disposed to protrude radially outward from the outer tube wall of the air duct.

[0014] In one or more embodiments, a diameter of the vent hole remains constant along the axial direction of the air duct.

[0015] In one or more embodiments, the air duct is connected to the outer surface of the low scroll shaft by welding.

[0016] On the other hand, according to some embodiments of the present application, a gas turbine engine is also provided, which particularly includes a core engine, wherein the core engine includes the low-turbine shaft assembly as described above.

[0017] On the other hand, according to some embodiments of the present application, a method for assembling a core engine is also provided, which comprises the following steps:

[0018] Providing an air conduit, wherein a plurality of vent holes are provided in the body of the air conduit;

[0019] The air duct is fixedly mounted on the outer periphery of the low-pressure turbine shaft of the low-pressure turbine assembly so that the air duct and the low-pressure turbine assembly form a low-pressure turbine assembly unit;

[0020] After assembling the combustion chamber and the high-pressure turbine assembly, assemble it with the high-pressure compressor;

[0021] The low-pressure turbine assembly unit is assembled with the assembled combustion chamber, the high-pressure turbine assembly and the high-pressure compressor.

[0022] The beneficial effects of the present invention are:

[0023] A low-vortex shaft assembly with such a configuration can eliminate the need to install the air duct in an engine with an existing configuration during assembly, and place the function of the air duct on the low-vortex shaft; thereby reducing the problems caused by assembly and disassembly of the air duct, shortening the engine assembly and disassembly cycle, and facilitating replacement for later repairs and maintenance.

[0024] The above description is only an overview of the technical solution of the present application. In order to more clearly understand the technical means of the present application, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Moreover, the same reference numerals are used throughout the drawings to represent the same components. In the drawings:

[0026] Figure 1 A schematic diagram of an existing high bypass ratio turbofan engine is shown;

[0027] Figure 2 A partial schematic diagram of an air duct in an existing high bypass ratio turbofan engine is shown;

[0028] Figure 3 Schematic diagrams of some embodiments of the low-turbulence shaft assembly are shown;

[0029] Figure 4 Schematic cross-sections of some embodiments of the present low-vortex shaft assembly are shown;

[0030] Figure 5 A schematic diagram schematically shows the assembly process according to the assembly method of the core engine;

[0031] Figure 6 A partial enlarged schematic diagram of one end of the air duct according to the present invention is shown;

[0032] Figure 7 A partially enlarged schematic diagram of the other end of the air duct according to the present invention is shown. DETAILED DESCRIPTION

[0033] The following embodiments of the technical solution of the present application are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, and are therefore only used as examples, and cannot be used to limit the scope of protection of the present application.

[0034] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0035] Figure 1 The schematic diagram of the existing high bypass ratio turbofan engine is shown. Figure 2 It is a partial schematic diagram of the air duct in the existing high bypass ratio turbofan engine. The turbofan engine includes an outer casing 90, a low-pressure compressor 91, a high-pressure compressor 92, a combustion chamber 93, a high-pressure turbine 94 and a low-pressure turbine 95. Among them, an air duct 97 is also provided on the outside of the low-pressure turbine shaft 96, and an air flow channel is provided inside the air duct 97 to separate the air flow entering the compressor into two streams, as shown by arrows 98 and 99. In the existing high bypass ratio turbofan engine, the two ends of the air duct 97 are respectively fixed to a certain stage of the compressor disk and the turbine rotor, which makes installation difficult.

[0036] In order to provide an air duct installation method that can reduce the problems caused by air duct assembly and disassembly and shorten the engine assembly and disassembly cycle, on the one hand, according to some embodiments of the present application, a low-turbo shaft assembly is provided, such as Figure 3 The schematic diagram of some embodiments of the low-turbo shaft assembly is shown, and the low-turbo shaft assembly includes a low-pressure turbine shaft 1 and an air duct 2. In the part shown in the figure, a high-pressure compressor 3, a combustion chamber 4 and a high-pressure turbine 5 are located outside the low-pressure turbine shaft 1.

[0037] Figure 4 A cross-sectional schematic diagram of some embodiments of the present low-pressure turbine shaft assembly is shown, wherein the air duct 2 is sleeved on the outer periphery of the low-pressure turbine shaft 1 and fixedly connected to the low-pressure turbine shaft 1 , and a plurality of ventilation holes 200 are opened in the pipe body 20 of the air duct 2 .

[0038] Combination Figure 3 as well as Figure 4 As shown, since a plurality of vent holes 200 are provided in the tube body 20 of the air duct 2, a cavity formed by the plurality of vent holes 200 is provided between the air duct 2 and the low-pressure turbine shaft 1, and the airflow entering the core engine can be divided into two parts by the air duct 2. A part of the airflow a passes through the hollow pipeline in the air duct 2 and is used to seal the middle and rear bearing cavities. The other part of the airflow b is formed between the outer peripheral surface of the air duct 2 and the high-pressure rotor and is used to cool the high-pressure vortex disk.

[0039] The low vortex shaft assembly having the above-mentioned configuration can save the following steps during assembly: Figure 1 to Figure 2 The installation requirements of the air duct in the engine of the configuration shown in the figure place the function of the air duct on the low turbine shaft; thereby reducing the problems caused by the assembly and disassembly of the air duct, shortening the engine assembly and disassembly cycle, and facilitating the replacement of the later repair and maintenance.

[0040] Specifically, on the other hand, according to some embodiments of the present application, a method for assembling a core engine is also provided, such as Figure 5The schematic diagram of the assembly process according to the assembly method of the core engine is schematically shown. The assembly method of the core engine includes the following steps:

[0041] First, an air duct 2 is provided. Figure 4 As shown, a plurality of ventilation holes 200 are provided in the tube body 20 .

[0042] Subsequently, the air duct 2 is fixedly installed on the outer periphery of the low-pressure turbine shaft 1 of the low-pressure turbine assembly, so that the air duct 2 and the low-pressure turbine assembly form a low-pressure turbine assembly unit 6.

[0043] After assembling the combustion chamber 4 with the high-pressure turbine assembly, assemble it with the high-pressure compressor 3;

[0044] The low-pressure turbine assembly unit 6 is assembled with the assembled combustion chamber 4, the high-pressure turbine assembly and the high-pressure compressor.

[0045] Through the above-mentioned assembly steps, in the actual assembly process, the combustion chamber and the high-vortex component are first combined, and then assembled with the high-pressure compressor. The air duct is assembled together with the low-vortex component, eliminating the step of blindly installing the air duct separately. At the same time, during the installation of the air duct 2, it can be assembled before the low-pressure turbine shaft 1 in a visible environment, which simplifies the assembly process, reduces the problems caused by the assembly and disassembly of the air duct, and shortens the engine assembly and disassembly cycle.

[0046] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0047] In the description of the embodiments of the present application, the term "plurality" refers to more than two (including two).

[0048] See also Figure 4 In some embodiments of the present low-vortex shaft assembly, the air duct 2 has an inner tube wall 21, an outer tube wall 22, and a tube body 20 surrounded by the inner tube wall 21 and the outer tube wall 22, and a plurality of air vents 200 are arranged in the tube body in a ring-shaped distribution along the circumference of the tube body 20. By having the air duct 2 with this configuration, it can be ensured that there is sufficient air inlet space inside the air duct 2.

[0049] Further, in some embodiments of the low-vortex shaft assembly, a plurality of ventilation holes 200 are evenly formed in the pipe body 20 along the circumferential direction c of the pipe body 20. By arranging the plurality of ventilation holes 200 evenly, the structural strength of the air duct 2 installed on the outer periphery of the low-vortex shaft 1 can be further ensured.

[0050] Figure 6 The figure shows a partially enlarged schematic view of one end of the air duct according to the present invention. Figure 7 The figure shows a partially enlarged schematic view of the other end of the air duct according to the present invention. In some embodiments of the low-vortex shaft assembly, sealing units 23 are provided at both ends of the air duct 2. The sealing units 23 protrude outward from the outer pipe wall 22 to form a sealing structure between the air duct 2 and the high-pressure compressor 3, and between the air duct 2 and the high-pressure turbine 5, so as to ensure the isolation of the mixing of the two airflows.

[0051] In some embodiments of the low-vortex shaft assembly, the sealing unit 23 is a labyrinth tooth protruding radially outward from the outer pipe wall 22 along the air duct. In some specific embodiments, the sealing unit 23 is a stepped labyrinth tooth seal, and a coating is provided on the corresponding high-pressure compressor 3 or high-pressure turbine 5 to achieve the labyrinth tooth sealing structure.

[0052] In some embodiments of the low-vortex shaft assembly, the sealing unit 23 is a brush seal protruding radially outward from the outer pipe wall 22 along the air duct. In some other suitable embodiments, the sealing unit 23 can also be a suitable sealing structure with other configurations.

[0053] In some embodiments of the low-vortex shaft assembly, the aperture of the ventilation hole 200 remains unchanged along the axial direction of the air duct 2, so that the ventilation hole 200 is an air extraction hole with an equal area as a whole, ensuring the smoothness of air extraction.

[0054] In some embodiments of the low-vortex shaft assembly, the air duct 2 is connected to the outer surface of the low-vortex shaft 1 by welding. In some other suitable embodiments, the air duct 2 can also be fixedly connected to the outer peripheral surface of the low-vortex shaft 1 by a suitable means such as a fastener.

[0055] On the other hand, according to some embodiments of the present application, a gas turbine engine is further provided, which includes a core engine, and the core engine includes the low-vortex shaft assembly as described in the previous one or more embodiments.

[0056] By configuring the low-vortex shaft assembly with this configuration, the installation requirement of the existing air duct in the current civil aviation engine can be cancelled, and the function of the air duct is placed on the low-vortex shaft. Therefore, the problems caused by the assembly and disassembly of the air duct can be reduced, the assembly and disassembly cycle of the engine can be shortened, and the replacement for later repair and maintenance is also facilitated.

[0057] In the description of the embodiments of the present application, the orientation or positional relationship indicated by the technical terms "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship of the connecting component in the connected state. It is only for the convenience of describing the embodiments of the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be understood as a limitation on the embodiments of the present application.

[0058] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0059] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them; although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application, and they should all be included in the scope of the claims and specification of the present application. In particular, as long as there is no structural conflict, the various technical features mentioned in the various embodiments can be combined in any way. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions that fall within the scope of the claims.

Claims

1. A low-turbo shaft assembly, It is characterized in that include: Low-pressure turbine shaft; as well as The air duct is sleeved on the outer periphery of the low-pressure turbine shaft and fixedly connected to the low-pressure turbine shaft. A plurality of vent holes are opened in the pipe body of the air duct.

2. The low-turbo shaft assembly according to claim 1, It is characterized in that The air duct comprises an inner tube wall, an outer tube wall and a tube body surrounded by the inner tube wall and the outer tube wall. The plurality of vents are arranged in the tube body in an annular distribution along the circumference of the tube body.

3. The low-turbo shaft assembly according to claim 2, It is characterized in that The plurality of vent holes are evenly arranged in the tube body along the circumference of the tube body.

4. The low-turbo shaft assembly according to claim 2, It is characterized in that Sealing units are arranged at both ends of the air duct, and the sealing units are arranged to protrude outward from the outer tube wall.

5. The low-turbo shaft assembly according to claim 4, It is characterized in that The sealing unit is a comb tooth which is arranged to protrude outward from the outer tube wall along the radial direction of the air duct.

6. The low-turbo shaft assembly according to claim 4, It is characterized in that The sealing unit is a brush seal which is arranged to protrude outward from the outer tube wall along the radial direction of the air duct.

7. The low-turbo shaft assembly according to claim 1, It is characterized in that The aperture of the vent hole remains constant along the axial direction of the air duct.

8. The low-turbo shaft assembly according to claim 1, It is characterized in that The air duct is connected to the outer surface of the low-turbine shaft by welding.

9. A gas turbine engine, It is characterized in that It comprises a core engine, wherein the core engine comprises a low-turbo shaft assembly as described in any one of claims 1 to 8.

10. A method for assembling a core engine, It is characterized in that The steps include: Providing an air conduit, wherein a plurality of vent holes are provided in the body of the air conduit; The air duct is fixedly mounted on the outer periphery of the low-pressure turbine shaft of the low-pressure turbine assembly so that the air duct and the low-pressure turbine assembly form a low-pressure turbine assembly unit; After assembling the combustion chamber and the high-pressure turbine assembly, assemble it with the high-pressure compressor; The low-pressure turbine assembly unit is assembled with the assembled combustion chamber, the high-pressure turbine assembly and the high-pressure compressor.

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