High-pressure rotor structure of small and medium-sized gas turbine

Abstract

A high-pressure rotor structure of a small and medium-sized gas turbine belongs to the technical field of gas turbines. The rotor structure solves the technical problems that an existing rotor structure is complex in structure, and consequently machining and assembling efficiency is low. Comprising a disc drum type compressor rotor and an axial flow single-stage cantilever type turbine rotor which are connected through a spline. The compressor rotor blades are connected with the compressor rotor wheel disc through dovetail groove type mortise and tenon joints; the front journal and the rear journal are located at the front end and the rear end of the disc-drum compressor rotor respectively, the gear sensor is installed at the front end of the front journal, the pipe is located in the middle of the circumference of the disc-drum compressor rotor, and an inclined hole communicated with the pipe is formed in the front journal. The turbine rotor blades and the turbine rotor wheel disc are connected through fir-tree-shaped mortise and tenon joints; the blocking pieces are arranged at the connecting positions of the turbine rotor blades and the turbine rotor wheel disc, and the axial displacement of the axial-flow single-stage cantilever type turbine rotor is limited through the blocking pieces. And the structure is reasonable, simple, reliable and light. The method is used for gas turbine design and manufacturing.

Description

Technical Field

[0001] This invention relates to a high-pressure rotor structure for small and medium-sized gas turbines, belonging to the field of gas turbine technology. Background Technology

[0002] A gas turbine works by compressing air to a certain pressure using a compressor, adding fuel in the combustion chamber to produce high-temperature gas, and then expanding the gas through a turbine to generate work. The high-pressure rotor's role is to convert the energy from the combustion chamber and stored in the high-temperature, high-pressure gas into mechanical work. A portion of this energy is used to drive the compressor to compress air, while the majority of the remaining energy serves as the gas turbine's effective work output. Traditional rotor structures, designed to meet high strength requirements, are relatively bulky, increasing the burden of assembly and transportation, and limiting the unit's application range. Furthermore, the oil and gas sealing structures and the air intake structures used to cool the high-temperature operating area are quite complex.

[0003] In summary, the existing rotor structure suffers from technical problems such as structural complexity, which leads to low processing and assembly efficiency. Summary of the Invention

[0004] This invention aims to solve the technical problem that the existing rotor structure is complex, resulting in low processing and assembly efficiency. Therefore, it proposes a high-pressure rotor structure for small and medium-sized gas turbines, which includes a disc-drum compressor rotor and an axial-flow single-stage cantilever turbine rotor connected by splines.

[0005] The disc compressor rotor includes a gear sensor, compressor rotor disc, compressor rotor blades, front journal, rear journal, and tube;

[0006] The compressor rotor blades and the compressor rotor disk are connected by dovetail joints;

[0007] The front journal and the rear journal are located at the front end and the rear end of the disc compressor rotor, respectively. The gear sensor is installed at the front end of the front journal, and the tube is located in the middle of the circumference of the disc compressor rotor. An oblique hole communicating with the tube is opened on the front journal.

[0008] The axial flow single-stage cantilever turbine rotor includes labyrinth seal comb teeth, turbine rotor journal, turbine rotor blades, baffles, dampers, and turbine rotor disc;

[0009] The turbine rotor blades and the turbine rotor disk are connected by fir tree-shaped tenon and mortise joints; baffles are set at the connection between the turbine rotor blades and the turbine rotor disk to limit the axial displacement of the axial flow single-stage cantilever turbine rotor.

[0010] Labyrinth seal combs are provided on both sides of the turbine rotor disk, on one side of the turbine rotor journal, and at the tip of the turbine rotor blades.

[0011] A damper is arranged in the groove between every two turbine rotor blades along the circumferential direction. The turbine rotor disk is connected to the turbine rotor journal, and the turbine rotor journal is connected to the rear journal by a spline.

[0012] As another improvement of the present invention, a high-pressure compressor front support assembly is installed at the front end of the disc compressor rotor.

[0013] The high-pressure compressor front support assembly includes, from front to back, a nut, a locking washer, a high-pressure compressor front support ball bearing, an oil baffle, a bushing, a sealing ring, and a labyrinth bushing.

[0014] As another improvement of the present invention, the compressor rotor disk and the compressor rotor blade are both designed to have ten stages. The first to third stage compressor rotor disks are formed into an integral structure by electron beam welding, and the fourth to seventh stage compressor rotor disks are formed into an integral structure by electron beam welding.

[0015] As another improvement of the present invention, a locking device is installed between the compressor rotor disc and the compressor rotor blades.

[0016] As another improvement of the present invention, a blind hole is designed at the tenon groove of the compressor rotor disk, and a pin is installed in the blind hole for counterweight.

[0017] As another improvement of the invention, a bearing is installed on the rear journal 19 to restrict air from entering the decompression chamber of the disc compressor.

[0018] As another improvement of the present invention, the rear axle journal 19 is also provided with a slide structure for mounting the bearing blocks.

[0019] As another improvement of the present invention, an air supply pipe is provided at the end of the compressor rotor disk cavity, and an oblique hole is provided on the air supply pipe to communicate with the turbine rotor disk cavity.

[0020] As another improvement of the present invention, an oblique air intake hole is provided below the turbine rotor blade for taking in air to cool the high-pressure turbine blade.

[0021] As another improvement of the present invention, the axial flow single-stage cantilever turbine rotor also includes bolts, locking plates and a second nut, and the turbine rotor disc and the turbine rotor journal are connected by bolts, locking plates and a second nut.

[0022] The beneficial effects of this invention are:

[0023] This invention features a reasonable and simple structure, reliable torque transmission, and lightweight construction, reducing manufacturing time and material costs. It incorporates a labyrinth seal air-sealing tooth structure to ensure system airtightness. The connection between the impeller and the moving blade is simple and reliable, reducing assembly burden. The structure includes a gear sensor that works in conjunction with a speed sensor to provide real-time speed information. A perforated tube structure for cooling is incorporated, providing functions such as cooling plate cavity, blades, and pressurization sealing. This design is simple, saves air volume, and improves unit efficiency. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of a high-pressure rotor structure for a small-to-medium-sized gas turbine according to the present invention.

[0025] Figure 2 This is a schematic diagram of an axial-flow single-stage cantilever turbine rotor structure.

[0026] Figure 3 This is a schematic diagram of a blind hole structure.

[0027] Figure 4 This is a schematic diagram of the compressor rotor disk and compressor rotor blades.

[0028] Figure 5 This is a schematic diagram of tile assembly. Detailed Implementation

[0029] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] Specific implementation method one: Combining Figures 1 to 5 This embodiment describes a high-pressure rotor structure for a small to medium-sized gas turbine, which includes a disc-drum compressor rotor and an axial-flow single-stage cantilever turbine rotor 23 connected by splines.

[0031] The disc compressor rotor includes a gear sensor 1, a compressor rotor disc 13, compressor rotor blades 9, a front journal 11, a rear journal 19, and a tube 12.

[0032] The compressor rotor blades 9 and the compressor rotor disk 13 are connected by a dovetail tenon joint;

[0033] The front journal 11 and the rear journal 19 are located at the front end and rear end of the disc compressor rotor, respectively. The gear sensor 1 is installed at the front end of the front journal 11. The tube 12 is located in the middle of the circumference of the disc compressor rotor. The front journal 11 has an oblique hole that communicates with the tube 12.

[0034] The axial flow single-stage cantilever turbine rotor 23 includes labyrinth seal comb teeth 23-1, turbine rotor journal 24, turbine rotor blades 23-7, baffles 23-6, damper 23-8, and turbine rotor disc 23-10;

[0035] The turbine rotor blades 23-7 and the turbine rotor disk 23-10 are connected by a fir tree-shaped tenon and mortise joint; the baffle 23-6 is set at the connection between the turbine rotor blades 23-7 and the turbine rotor disk 23-10, and the axial displacement of the axial flow single-stage cantilever turbine rotor 23 is restricted by the baffle 23-6.

[0036] Labyrinth sealing combs 23-1 are provided on both sides of the turbine rotor disk 23-10, on one side of the turbine rotor journal 24, and at the tip of the turbine rotor blade 23-7.

[0037] A damper 23-8 is arranged in the groove between every two turbine rotor blades 23-7 along the circumferential direction. The turbine rotor disc 23-10 is connected to the turbine rotor journal 24. The turbine rotor journal 24 is connected to the rear journal 19 by a spline.

[0038] A high-pressure turbine compressor gear sensor 1 is installed on the front axle journal 11. Together with a speed sensor installed on the gas turbine casing, it can accurately reflect the actual rotational speed of the rotor. After the gas turbine completes the ignition process, air is compressed by the compressor and supplied to the combustion chamber to provide sufficient oxygen. After the natural gas is burned in the combustion chamber, the high-temperature and high-pressure gas acts on the high-pressure turbine rotor. The high-pressure turbine rotor and the high-pressure compressor rotor are connected by a spline to transmit torque, which in turn drives the compressor to continue compressing gas and supplying oxygen.

[0039] The air is compressed from left to right, passing through the compressor, combustion chamber, turbine, and power turbine in sequence.

[0040] During operation, the high-pressure gas at the flow path flows through the air holes of the first and second stage wheel disks into the disk cavity to cool the wheel disk cavity. The airflow passes through the oblique hole of the front axle journal and enters the tube, blowing towards the low-pressure compressor to cool the low-pressure rotor system on one hand, and towards the high-pressure turbine to cool the high-temperature working area on the other hand.

[0041] Air intake holes are provided on the fourth, fifth, sixth, seventh, and eighth stage rotor discs to draw in the unit's circulating gas and blow it into the rotor disc chamber to cool the disc chamber. An oblique hole matching pipe system is provided at the air supply pipe at the end of the disc chamber to guide the gas in the rotor disc chamber into the high-pressure turbine rotor disc chamber to cool the high-temperature working area.

[0042] An oblique air intake hole is provided below the moving blade of the high-pressure turbine disk to draw air and blow it to cool the high-pressure turbine blades. In conjunction with the hole system inside the blades, it effectively cools the blades in the high-temperature zone and extends their service life.

[0043] The rotor disc is made of GH4698 forgings, which are rough-machined and then annealed.

[0044] The moving blade is made of TC11 precision forging. After rough machining, it is pickled, then stabilized and annealed, and shot peened. The surface of the moving blade root and the dovetail groove of the wheel is silver-plated.

[0045] Before press-fitting, heat the containment disc to 200°C; when assembling the connecting pins, heat the disc to 300°C.

[0046] Specific Implementation Method Two: Combining Figures 1 to 5 This embodiment differs from Specific Embodiment 1 in that a high-pressure compressor front support assembly is installed at the front end of the disc compressor rotor.

[0047] The high-pressure compressor front support assembly includes, from front to back, a first nut 2, a locking washer 3, a high-pressure compressor front support ball bearing 4, an oil baffle ring 5, a bushing 6, a sealing ring 7, and a labyrinth bushing 8.

[0048] The front support housing of the high-pressure compressor contains ball bearings, which are lubricated by oil guide rings. To ensure internal oil supply, an injector supplies oil to the ball bearings through channels in the front journal of the high-pressure turbo compressor rotor and the oil baffle channel.

[0049] The oil chamber is sealed from the high-pressure compressor side by a sealing ring, which forms a radial end contact seal with the bushing and the oil baffle ring.

[0050] A labyrinth bushing 8 is designed behind the ball bearing of the front support of the high-pressure compressor to prevent lubricating oil and oil-gas from entering the rotor system. Other components and connections are the same as in Specific Embodiment 1.

[0051] Specific implementation method three: Combining Figures 1 to 5 This embodiment differs from specific embodiment one in that both the compressor rotor disk 13 and the compressor rotor blade 9 are designed with ten stages. The first to third stage compressor rotor disks 13 are formed into an integral structure by electron beam welding, and the fourth to seventh stage compressor rotor disks 13 are formed into an integral structure by electron beam welding.

[0052] Symmetrically arranged disassembly ports are designed at the connection end faces of the first and second level wheel discs, the fourth to eighth level wheel discs, the front journal 11, and the rear journal 19. The disassembly ports are semi-circular arc-shaped to reduce stress concentration.

[0053] To ensure rotor rotational balance, initially, each stage of the rotor, including the front and rear journals, undergoes high-speed dynamic balancing. Then, the first and second stage rotors, and the fourth to eighth stage rotors, are welded together and subjected to high-speed dynamic balancing. Finally, after assembly into the compressor rotor, it undergoes another high-speed dynamic balancing process. Other components and connection methods are the same as in specific implementation methods one or two.

[0054] Specific implementation method four: Combination Figures 1 to 5 This embodiment differs from specific embodiment one in that a locking device 10 is installed between the compressor rotor disc 13 and the compressor rotor blades 9. This ensures a reliable connection between the compressor rotor disc 13 and the compressor rotor blades 9. The compressor rotor blades are tenon-and-mortise connected to the compressor rotor disc with a dovetail-shaped structure. End face positioning is achieved by the locking device 10 located in the middle, which engages with a pre-drilled circular hole in the disc's tenon groove. The locking plate's end is folded into a pre-drilled groove on the blade end face, completing the assembly and fixing. Other components and connection methods are the same as in any one of specific embodiments one to three.

[0055] Specific Implementation Method Five: Combining Figures 1 to 5 This embodiment differs from specific embodiment one in that the compressor rotor disc 13 has a blind hole 14 at the tenon groove, and a pin is installed in the blind hole 14 for counterweight. Other components and connection methods are the same as any one of specific embodiments one to four.

[0056] Specific Implementation Method Six: Combination Figures 1 to 5 This embodiment differs from specific embodiment one in that a bearing 17 is installed on the rear journal 19 to restrict air from entering the decompression chamber of the disc compressor rotor. This, combined with the labyrinth seal at the dynamic-static connection of the unit, further restricts air from entering the decompression chamber after the high-pressure compressor, reducing the manufacturing difficulty and maintenance cost of the rear journal. Other components and connections are the same as in any one of specific embodiments one through five.

[0057] Specific implementation method seven: Combining Figures 1 to 5 This embodiment differs from specific embodiment one in that it also includes a sliding track structure for mounting the bearing pad 17 on the rear axle journal 19. After installation, it is fixed and limited with pins to prevent vibration and wear of the rotating parts during operation. Other components and connection methods are the same as any one of specific embodiments one to six.

[0058] Specific implementation method eight: Combination Figures 1 to 5This embodiment differs from specific embodiment one in that a gas supply pipe is provided at the end of the compressor rotor disk 13, and the gas supply pipe has an oblique hole communicating with the disk cavity of the turbine rotor disks 23-10. The oblique hole and matching pipe system at the end of the disk cavity of the gas supply pipe guide the gas in the rotor disk cavity to the high-pressure turbine rotor disk cavity to cool the high-temperature working area. Other components and connection methods are the same as any one of specific embodiments one to seven.

[0059] Specific Implementation Method Nine: Combining Figures 1 to 5 This embodiment differs from specific embodiment one in that it has an air intake oblique hole below the turbine rotor blades 23-7 for intake air to cool the high-pressure turbine blades. This effectively cools the blades in the high-temperature zone, extending their service life. Other components and connection methods are the same as any one of specific embodiments one through eight.

[0060] Specific Implementation Method Ten: Combining Figures 1 to 5 This embodiment differs from specific embodiment one in that the axial flow single-stage cantilever turbine rotor 23 further includes bolts 23-3, locking plates 23-4, and a second nut 23-5. The turbine rotor disc 23-10 is connected to the turbine rotor journal 24 via bolts 23-3, locking plates 23-4, and a second nut 23-5. The structure is stable and reliable. Other components and connection methods are the same as any one of specific embodiments one to nine.

[0061] Combination Figures 1 to 5 Explanation of the working principle of this invention:

[0062] After the gas turbine completes ignition, air is compressed by the compressor and supplied to the combustion chamber, providing sufficient oxygen. After combustion in the combustion chamber, the high-temperature, high-pressure gas acts on the high-pressure turbine rotor. The high-pressure turbine rotor and the high-pressure compressor rotor are connected by a spline for torque transmission, which in turn drives the compressor to continue compressing and supplying oxygen. The compression direction is from left to right, passing through the compressor, combustion chamber, turbine, and power turbine in sequence.

[0063] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A high-pressure rotor structure for a small to medium-sized gas turbine, characterized in that... It includes a disc-drum compressor rotor and an axial-flow single-stage cantilever turbine rotor (23) connected by splines. The disc compressor rotor includes a gear sensor (1), a compressor rotor disc (13), compressor rotor blades (9), a front journal (11), a rear journal (19), and a tube (12). The compressor rotor blades (9) and the compressor rotor disc (13) are connected by dovetail tenon joints; The front journal (11) and the rear journal (19) are located at the front end and rear end of the disc compressor rotor, respectively. The gear sensor (1) is installed at the front end of the front journal (11). The tube (12) is located in the middle of the circumference of the disc compressor rotor. An oblique hole communicating with the tube (12) is opened on the front journal (11). The axial flow single-stage cantilever turbine rotor (23) includes labyrinth seal comb teeth (23-1), turbine rotor journal (24), turbine rotor blades (23-7), baffles (23-6), damper (23-8) and turbine rotor disc (23-10). The turbine rotor blades (23-7) and the turbine rotor disk (23-10) are connected by a fir tree-shaped tenon and mortise joint; baffles (23-6) are set at the connection between the turbine rotor blades (23-7) and the turbine rotor disk (23-10), and the axial displacement of the axial flow single-stage cantilever turbine rotor (23) is restricted by the baffles (23-6); Labyrinth sealing combs (23-1) are provided on both sides of the turbine rotor disk (23-10), on one side of the turbine rotor journal (24), and at the tip of the turbine rotor blade (23-7). A damper (23-8) is arranged in the groove between every two turbine rotor blades (23-7) along the circumferential direction. The turbine rotor disc (23-10) is connected to the turbine rotor journal (24), and the turbine rotor journal (24) is connected to the rear journal (19) by a spline.

2. The high-pressure rotor structure for a small to medium-sized gas turbine according to claim 1, characterized in that, The front end of the disc compressor rotor is equipped with a high-pressure compressor front support assembly. The high-pressure compressor front support assembly includes a first nut (2), a retaining washer (3), a high-pressure compressor front support ball bearing (4), an oil baffle (5), a bushing (6), a sealing ring (7), and a labyrinth bushing (8), arranged from front to back.

3. The high-pressure rotor structure for a small to medium-sized gas turbine according to claim 1, characterized in that, The compressor rotor disk (13) and compressor rotor blade (9) are both designed with ten stages. The first to third stage compressor rotor disks (13) are formed into an integral structure by electron beam welding, and the fourth to seventh stage compressor rotor disks (13) are formed into an integral structure by electron beam welding.

4. The high-pressure rotor structure for a small to medium-sized gas turbine according to claim 1, characterized in that, A locker (10) is installed between the compressor rotor disc (13) and the compressor rotor blade (9).

5. The high-pressure rotor structure for a small to medium-sized gas turbine according to claim 1, characterized in that, The compressor rotor disc (13) has a blind hole (14) at the tenon groove, and a pin is installed in the blind hole (14) for counterweight.

6. The high-pressure rotor structure for a small to medium-sized gas turbine according to claim 1, characterized in that, A bearing (17) is installed on the rear journal (19) to restrict air from entering the decompression chamber of the disc compressor rotor.

7. The high-pressure rotor structure for a small to medium-sized gas turbine according to claim 6, characterized in that, The rear journal (19) is also provided with a slide structure for mounting the bearing (17).

8. The high-pressure rotor structure for a small to medium-sized gas turbine according to claim 1, characterized in that, An air supply pipe is provided at the end of the cavity of the compressor rotor disk (13), and an oblique hole is provided on the air supply pipe to communicate with the cavity of the turbine rotor disk (23-10).

9. The high-pressure rotor structure for a small to medium-sized gas turbine according to claim 1, characterized in that, An oblique air intake hole is provided below the turbine rotor blade (23-7) for taking in air to cool the high-pressure turbine blade.

10. A high-pressure rotor structure for a small to medium-sized gas turbine according to claim 1, characterized in that, The axial flow single-stage cantilever turbine rotor (23) also includes bolts (23-3), locking plates (23-4) and a second nut (23-5). The turbine rotor disc (23-10) and the turbine rotor journal (24) are connected by bolts (23-3), locking plates (23-4) and a second nut (23-5).

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