Gas turbine rotor system

Abstract

The invention discloses a gas turbine rotor system which comprises a rotating shaft, a gas compression assembly, a turbine assembly and a torque assembly, the rotating shaft extends in the first direction, the gas compression assembly is arranged on the rotating shaft, the rotating shaft can rotate around the first direction relative to the gas compression assembly, the gas compression assembly is used for compressing gas, and the turbine assembly is arranged on the rotating shaft. The turbine assembly is arranged on the rotating shaft, the rotating shaft can rotate around the first direction relative to the turbine assembly, the turbine assembly is used for doing work through compressed gas, the torque assembly is arranged on the rotating shaft, the mass of the torque assembly is adjustable, and the torque of the turbine assembly can be adjusted by adjusting the mass of the torque assembly. And the mass of the rotating shaft is changed. The gas turbine rotor system is good in stability and high in safety.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine rotor system. Background Art

[0002] When rotating at high speeds, heavy-duty gas turbines or aircraft engines are subject to gyroscopic torque effects induced by the high-speed field, significantly altering their dynamic characteristics compared to a stationary state. Gyroscopic torque can cause radial deflection and bending stress in the rotating shaft, reducing the clearance between the rotor blades and the cylinder, weakening the shaft's strength, and shortening its lifespan. In the aircraft engine field, to mitigate the effects of gyroscopic torque, counter-rotating high- and low-pressure rotors are often used to offset some of the gyroscopic torque, minimizing shaft deflection and bending stress, and thus reducing its impact on the engine.

[0003] However, in the existing technology, heavy-duty gas turbines mostly adopt a single-rotor design, and are unable to use a counter-rotating design of high- and low-pressure rotor sets to offset the influence of some gyroscopic torques, resulting in a reduction in the service life of the heavy-duty gas turbines. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems in the related art to a certain extent. To this end, an embodiment of the present invention provides a gas turbine rotor system with good stability and high safety.

[0005] A gas turbine rotor system according to an embodiment of the present invention includes:

[0006] a rotating shaft extending along a first direction;

[0007] a gas compression assembly, the gas compression assembly being disposed on the rotating shaft, the rotating shaft being rotatable about the first direction relative to the gas compression assembly, and the gas compression assembly being used to compress gas;

[0008] a turbine assembly, the turbine assembly being disposed on the rotating shaft, the rotating shaft being rotatable relative to the turbine assembly about the first direction, the turbine assembly being configured to utilize the compressed gas to perform work;

[0009] A torque component is provided on the rotating shaft. The mass of the torque component is adjustable. By adjusting the mass of the torque component, the mass of the rotating shaft can be changed.

[0010] The gas turbine rotor system of an embodiment of the present invention adjusts the overall mass of the shaft by arranging a torque assembly on the shaft, thereby reducing flexural deformation and bending stress during the rotation of the shaft, thereby ensuring the rotor system's ability to resist interference and stability. Furthermore, by adjusting the mass of the torque assembly, the critical speed of the rotor system can be adjusted, optimizing the design and balance of the rotor system, improving safety, and reducing vibration and noise.

[0011] In some embodiments, the torque assembly includes a torque disc and an adjusting member, the torque disc is passed through the rotating shaft, and the adjusting member is detachably provided on the torque disc. There are multiple adjusting members, and the mass of the torque assembly can be adjusted by adjusting the number of adjusting members on the torque disc.

[0012] In some embodiments, there are at least two torque discs, and at least two of the torque discs are spaced apart along the first direction.

[0013] In some embodiments, the torque disk has a plurality of insertion holes, which are arranged at intervals around the circumference of the torque disk, and the adjusting member is detachably disposed in the insertion holes.

[0014] In some embodiments, the inner wall surface of the socket has an internal thread, the outer wall surface of the adjusting member has an external thread, and the adjusting member is threadedly matched with the inner wall surface of the socket.

[0015] In some embodiments, the adjustment member is a screw.

[0016] In some embodiments, the rotating shaft includes a first rotating shaft and a second rotating shaft, the first rotating shaft and the second rotating shaft are rotatably connected, the central axis of the first rotating shaft and the central axis of the second rotating shaft are collinear, the torque assembly is arranged on the first rotating shaft, a part of the compressor assembly is arranged on the first rotating shaft, another part of the compressor assembly is arranged on the second rotating shaft, and the turbine assembly is arranged on the second rotating shaft.

[0017] In some embodiments, the air compressor assembly includes a low-pressure compressor and a high-pressure compressor, the low-pressure compressor includes an intake cylinder, a low-pressure compressor cylinder, and an exhaust volute sequentially arranged on the first rotating shaft, the high-pressure compressor includes an intake volute and a high-pressure compressor cylinder sequentially arranged on the second rotating shaft, and an intercooler heat recovery device is provided between the exhaust volute and the intake volute.

[0018] The turbine assembly includes a combustion chamber, a turbine cylinder and an exhaust cylinder which are sequentially arranged on the second rotating shaft. External gas enters the intake cylinder, the low-pressure compressor cylinder, the exhaust volute, the intercooler and heat recovery device, the intake volute and the high-pressure compressor cylinder in sequence for compression. The compressed gas enters the combustion chamber for combustion and is then discharged from the exhaust cylinder through the turbine cylinder.

[0019] In some embodiments, the gas turbine rotor system further includes a planetary gear transmission, wherein the planetary gear transmission is disposed between the first rotating shaft and the second rotating shaft.

[0020] In some embodiments, the gas turbine rotor system further comprises:

[0021] a first bearing, the first bearing being disposed between the intake cylinder and the first rotating shaft so as to enable the first rotating shaft to rotate relative to the intake cylinder;

[0022] a second bearing disposed between the exhaust volute and the first rotating shaft so as to allow the first rotating shaft to rotate relative to the exhaust volute;

[0023] a third bearing, the third bearing being provided between the intake volute and the second rotating shaft so as to enable the second rotating shaft to rotate relative to the intake volute;

[0024] A fourth bearing is provided between the exhaust cylinder and the second rotating shaft so that the second rotating shaft can rotate relative to the exhaust cylinder. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 Schematic diagram of a gas turbine rotor system according to an embodiment of the present invention.

[0026] Figure 2 yes Figure 1 Enlarged schematic diagram of part A.

[0027] Figure 3 Schematic diagram of a torque assembly of a gas turbine rotor system according to an embodiment of the present invention.

[0028] Figure numerals: 1. rotating shaft; 11. first rotating shaft; 12. second rotating shaft; 2. compressor assembly; 21. low-pressure compressor; 211. intake cylinder; 212. low-pressure compressor cylinder; 213. exhaust volute; 22. high-pressure compressor; 221. intake volute; 222. high-pressure compressor cylinder; 23. intercooler and heat recovery device; 3. turbine assembly; 31. combustion chamber; 32. turbine cylinder; 33. exhaust cylinder; 4. torque assembly; 41. torque plate; 411. through hole; 412. socket; 42. adjusting part; 5. planetary gear transmission; 61. first bearing; 62. second bearing; 63. third bearing; 64. fourth bearing. DETAILED DESCRIPTION

[0029] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0030] like Figure 1-Figure 3As shown, a gas turbine rotor system according to an embodiment of the present invention includes a rotating shaft 1, a compressor assembly 2, a turbine assembly 3, and a torque assembly 4. The rotating shaft 1 extends in a first direction. The compressor assembly 2 is disposed on the rotating shaft 1 and is rotatable relative to the compressor assembly 2 in the first direction. The compressor assembly 2 is used to compress gas. The turbine assembly 3 is disposed on the rotating shaft 1 and is rotatable relative to the turbine assembly 3 in the first direction. The turbine assembly 3 is used to generate work using the compressed gas. The torque assembly 4 is disposed on the rotating shaft 1. The mass of the torque assembly 4 is adjustable. By adjusting the mass of the torque assembly 4, the mass of the rotating shaft 1 can be changed.

[0031] The gas turbine rotor system of an embodiment of the present invention adjusts the overall mass of the shaft 1 by providing a torque assembly 4 on the shaft 1, thereby reducing flexural deformation and bending stress during the rotation of the shaft 1, thereby ensuring the rotor system's ability to resist interference and stability. Furthermore, by adjusting the mass of the torque assembly 4, the critical speed of the rotor system can be adjusted, optimizing the design and balance of the rotor system, improving safety, and reducing vibration and noise.

[0032] In some embodiments, the torque assembly 4 includes a torque disc 41 and an adjusting member 42. The torque disc 41 is passed through the rotating shaft 1. The adjusting member 42 is detachably provided on the torque disc 41. There are multiple adjusting members 42. The mass of the torque assembly 4 can be adjusted by adjusting the number of adjusting members 42 on the torque disc 41.

[0033] Specifically, the torque disc 41 is annular, with a circular outer contour. A through-hole 411 is provided in the middle of the torque disc 41, through which the torque disc 41 is mounted on the rotating shaft 1. The adjusting member 42 is detachably mounted on the torque disc 41, making it easy to adjust the number of adjusting members 42 on the torque disc 41 and convenient to operate.

[0034] In some embodiments, there are at least two torque disks 41 , and the at least two torque disks 41 are spaced apart along the first direction.

[0035] Specifically, at least two torque discs 41 are arranged on the rotating shaft 1 at intervals along the first direction to meet the need of changing the critical speed of the gas turbine rotor system.

[0036] In some embodiments, the torque disk 41 has a plurality of insertion holes 412 , which are arranged at intervals around the circumference of the torque disk 41 , and the adjustment member 42 is detachably disposed in the insertion holes 412 .

[0037] Specifically, multiple sockets 412 are evenly spaced along the circumference of the torque disk 41, and the multiple sockets 412 correspond one-to-one to the multiple adjustment members 42. The adjustment members 42 are detachably arranged in the sockets 412 for easy operation. Moreover, by adjusting the number of adjustment members 42 inserted into the sockets 412, the mass of the torque assembly 4 is changed, thereby providing a certain range of variation for changing the critical speed of the gas turbine rotor system.

[0038] In some embodiments, the inner wall of the jack 412 has an internal thread, and the outer wall of the adjusting member 42 has an external thread. The adjusting member 42 and the inner wall of the jack 412 are threaded together, which makes the installation method simple and easy to assemble and disassemble.

[0039] In some embodiments, the adjusting member 42 is a screw, and the adjusting member 42 has a simple structure and saves costs.

[0040] In some embodiments, the rotating shaft 1 includes a first rotating shaft 11 and a second rotating shaft 12, the first rotating shaft 11 and the second rotating shaft 12 are rotatably connected, the central axis of the first rotating shaft 11 is collinear with the central axis of the second rotating shaft, the torque assembly 4 is arranged on the first rotating shaft 11, a part of the compressor assembly 2 is arranged on the first rotating shaft 11, another part of the compressor assembly 2 is arranged on the second rotating shaft 12, and the turbine assembly 3 is arranged on the second rotating shaft 12.

[0041] Specifically, the first rotating shaft 11 is a low-pressure rotor, and the second rotating shaft 12 is a high-pressure rotor. The rotation directions of the first rotating shaft 11 and the second rotating shaft 12 are the same, and the rotation speeds of the first rotating shaft 11 and the second rotating shaft 12 may be different. By arranging a torque component 4 on the first rotating shaft 11 to offset the gyroscopic torque generated by the uneven mass distribution of the first rotating shaft 11 and the second rotating shaft 12, compared with the prior art, the flexural deformation and bending stress of the rotating shaft 1 are reduced, and the influence of the gyroscopic torque on the engine is reduced.

[0042] In some embodiments, the compressor assembly 2 includes a low-pressure compressor 21 and a high-pressure compressor 22. The low-pressure compressor 21 includes an intake cylinder 211, a low-pressure compressor 21 cylinder, and an exhaust volute 213, which are sequentially arranged on the first rotating shaft 11. The high-pressure compressor 22 includes an intake volute 221 and a high-pressure compressor 22 cylinder, which are sequentially arranged on the second rotating shaft 12. An intercooler and heat recovery device 23 is provided between the exhaust volute 213 and the intake volute 221. The turbine assembly 3 includes a combustion chamber 31, a turbine cylinder 32, and an exhaust cylinder 33, which are sequentially arranged on the second rotating shaft 12.

[0043] The external gas enters the intake cylinder 211, the low-pressure compressor cylinder 21, the exhaust volute 213, the intercooler and heat recovery device 23, the intake volute 221 and the high-pressure compressor cylinder 22 in sequence for compression. The compressed gas enters the combustion chamber 31 for combustion, and then passes through the turbine cylinder 32 and is discharged from the exhaust cylinder 33.

[0044] Specifically, air is supplied to the compressor assembly 2 and compressed into compressed air of higher pressure and temperature. The compressed air then flows into the combustion chamber 31 and mixes and burns with the fuel in the combustion chamber 31 to form a high-temperature, high-pressure, high-speed gas flow. The gas flow flows into the turbine cylinder 32 and drives the turbine cylinder 32 to rotate to output mechanical work. Finally, the air is discharged through the exhaust cylinder 33.

[0045] In some embodiments, the gas turbine rotor system further includes a planetary gear transmission 5 , which is disposed between the first rotating shaft 11 and the second rotating shaft 12 to ensure that the first rotating shaft 11 and the second rotating shaft 12 are concentric and can achieve different speeds of the first rotating shaft 11 and the second rotating shaft 12 .

[0046] In some embodiments, the gas turbine rotor system further includes a first bearing 61, a second bearing 62, a third bearing 63, and a fourth bearing 64. The first bearing 61 is disposed between the intake cylinder 211 and the first rotating shaft 11 to enable the first rotating shaft 11 to rotate relative to the intake cylinder 211. The second bearing 62 is disposed between the exhaust volute 213 and the first rotating shaft 11 to enable the first rotating shaft 11 to rotate relative to the exhaust volute 213. The third bearing 63 is disposed between the intake volute 221 and the second rotating shaft 12 to enable the second rotating shaft 12 to rotate relative to the intake volute 221. The fourth bearing 64 is disposed between the exhaust cylinder 33 and the second rotating shaft 12 to enable the second rotating shaft 12 to rotate relative to the exhaust cylinder 33.

[0047] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0048] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0049] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0050] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0051] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0052] Although the above embodiments have been shown and described, it is understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those skilled in the art are all within the scope of protection of the present invention.

Claims

1. A gas turbine rotor system, characterized in that: include: A rotating shaft (1), the rotating shaft (1) extending along a first direction; A gas compression component (2), the gas compression component (2) being arranged on the rotating shaft (1), the rotating shaft (1) being rotatable about the first direction relative to the gas compression component (2), and the gas compression component (2) being used for compressing gas; a turbine assembly (3), the turbine assembly (3) being arranged on the rotating shaft (1), the rotating shaft (1) being rotatable about the first direction relative to the turbine assembly (3), and the turbine assembly (3) being used to perform work using compressed gas; A torque component (4) is provided on the rotating shaft (1); the mass of the torque component (4) is adjustable; and the mass of the rotating shaft (1) is changed by adjusting the mass of the torque component (4).

2. The gas turbine rotor system according to claim 1, characterized in that The torque assembly (4) comprises a torque disc (41) and an adjusting member (42), wherein the torque disc (41) is passed through the rotating shaft (1), and the adjusting member (42) is detachably arranged on the torque disc (41). There are a plurality of adjusting members (42), and the mass of the torque assembly (4) can be adjusted by adjusting the number of adjusting members (42) on the torque disc (41).

3. The gas turbine rotor system according to claim 2, characterized in that: There are at least two torque discs (41), and at least two of the torque discs (41) are spaced apart along the first direction.

4. The gas turbine rotor system according to claim 2, wherein: The torque disc (41) is provided with a plurality of insertion holes (412), which are arranged at intervals around the circumference of the torque disc (41). The adjusting member (42) is detachably arranged in the insertion holes (412).

5. The gas turbine rotor system according to claim 4, characterized in that: The inner wall surface of the insertion hole (412) has an internal thread, the outer wall surface of the adjustment member (42) has an external thread, and the adjustment member (42) is threadedly matched with the inner wall surface of the insertion hole (412).

6. The gas turbine rotor system according to any one of claims 2 to 5, characterized in that: The adjusting member (42) is a screw.

7. The gas turbine rotor system according to claim 1, wherein: The rotating shaft (1) includes a first rotating shaft (11) and a second rotating shaft (12), wherein the first rotating shaft (11) and the second rotating shaft (12) are rotatably connected, and the central axis of the first rotating shaft (11) and the central axis of the second rotating shaft (12) are collinear, the torque component (4) is arranged on the first rotating shaft (11), a part of the compressor component (2) is arranged on the first rotating shaft (11), and another part of the compressor component (2) is arranged on the second rotating shaft (12), and the turbine component (3) is arranged on the second rotating shaft (12).

8. The gas turbine rotor system according to claim 7, characterized in that: The compression assembly (2) includes a low-pressure compressor (21) and a high-pressure compressor (22), wherein the low-pressure compressor (21) includes an intake cylinder (211), a low-pressure compressor (21) cylinder, and an exhaust volute (213) sequentially arranged on the first rotating shaft (11), and the high-pressure compressor (22) includes an intake volute (221) and a high-pressure compressor (22) cylinder sequentially arranged on the second rotating shaft (12), and an intercooling heat recovery device (23) is provided between the exhaust volute (213) and the intake volute (221). The turbine assembly (3) includes a combustion chamber (31), a turbine cylinder (32) and an exhaust cylinder (33) which are sequentially arranged on the second rotating shaft (12). External gas sequentially enters the intake cylinder (211), the low-pressure compressor (21) cylinder, the exhaust volute (213), the intercooling and heat recovery device (23), the intake volute (221) and the high-pressure compressor (22) cylinder for compression. The compressed gas enters the combustion chamber (31) for combustion and is then discharged from the exhaust cylinder (33) through the turbine cylinder (32).

9. The gas turbine rotor system according to claim 7, characterized in that: It also includes a planetary gear transmission (5), which is arranged between the first rotating shaft (11) and the second rotating shaft (12).

10. The gas turbine rotor system according to claim 8, wherein: Also includes: a first bearing (61), the first bearing (61) being provided between the air intake cylinder (211) and the first rotating shaft (11), so that the first rotating shaft (11) can rotate relative to the air intake cylinder (211); a second bearing (62), the second bearing (62) being provided between the exhaust volute (213) and the first rotating shaft (11), so that the first rotating shaft (11) can rotate relative to the exhaust volute (213); a third bearing (63), the third bearing (63) being provided between the air intake volute (221) and the second rotating shaft (12), so that the second rotating shaft (12) can rotate relative to the air intake volute (221); A fourth bearing (64) is provided between the exhaust cylinder (33) and the second rotating shaft (12) so that the second rotating shaft (12) can rotate relative to the exhaust cylinder (33).

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