Double-sided composite turbine generator with adjustable guide vanes

Abstract

The invention discloses a double-sided composite turbine generator with adjustable guide vanes. Comprising a double-face composite turbine mechanism, a coil winding arranged on the double-face composite turbine mechanism in a sleeving mode, an interstage gas pipeline arranged on the coil winding in a sleeving mode, an annular combustion chamber communicated with the interstage gas pipeline, a gas conveying channel arranged on the interstage gas pipeline in a sleeving mode and an adjustable guide vane mechanism arranged at an inlet of a double-stage hollow turbine blade disc. Compared with the prior art, the axial size of a turbine generator system is greatly reduced, efficient cooling of the turbine blades is achieved through the double-face composite gas compressor structure, the heat efficiency of the generator is improved, and the turbine power generation output response is improved through the adjustable guide vanes.

Description

Technical Field

[0001] The invention relates to the technical field of generators, and in particular to a double-sided compound turbine generator with adjustable guide vanes. Background Art

[0002] Micro-aircraft, especially swarm drones and special expendable drones, need to adopt power devices with high energy / power density, small size, light weight, safety, reliability, low cost and other technical requirements. However, the existing micro-turbine generator technology is difficult to meet the performance requirements of future micro-aircraft such as high Mach number, long flight time, and high payload. Looking at the current status of micro-turbine generator research, it is an inevitable trend to develop micro-turbine generators with compact and lightweight structure, low cost, high aerodynamic performance, and high cycle parameters. Therefore, it is necessary to develop a new generator to solve the above problems. Summary of the invention

[0003] Purpose of the invention: To solve the above problems, the present invention provides a double-sided compound turbine generator with adjustable guide vanes, which greatly reduces the axial dimension, makes the generator coaxiality and vibration reduction effect good, and uses the double-sided compound turbine structure to cool the turbine blades, improves the thermal efficiency of the generator, and uses adjustable guide vanes to improve the turbine power generation output response.

[0004] Technical solution: To achieve the above-mentioned purpose, the double-sided compound turbine generator with adjustable guide vanes described in the present invention includes a double-sided compound turbine mechanism, a coil winding sleeved on the double-sided compound turbine mechanism, an interstage gas pipeline sleeved on the coil winding, an annular combustion chamber connected to the interstage gas pipeline, a gas transmission channel sleeved on the interstage gas pipeline, and an adjustable guide vane mechanism; the double-sided compound turbine mechanism includes a front fairing, a first centrifugal compressor connected to the front fairing, a first ring connected to the outer periphery of the first centrifugal compressor, a first hollow turbine blade connected to the outer periphery of the first ring, and a first hollow turbine blade connected to the first hollow turbine blade. A second circular ring connected to the core turbine blades, a rear fairing, a connecting shaft located between the front fairing and the rear fairing, a second centrifugal compressor connected to the rear fairing, a third circular ring connected to the outer periphery of the second centrifugal compressor, a second hollow turbine blade connected to the outer periphery of the third circular ring, and a fourth circular ring connected to the outer periphery of the second hollow turbine blade; the front fairing, the connecting shaft, and the rear fairing are coaxially connected in sequence; the coil winding is sleeved on the outer periphery of the connecting shaft; one end of the air delivery channel is connected to the annular combustion chamber, and the other end is connected to the second hollow turbine blade; the annular combustion chamber is also connected to the first hollow turbine blade.

[0005] Furthermore, the first circular ring, the second circular ring and the first hollow turbine blade form a first hollow turbine blade disk.

[0006] Furthermore, the third circular ring, the fourth circular ring and the second hollow turbine blades form a second hollow turbine blade disk.

[0007] Furthermore, the first hollow turbine blade disk and the second hollow turbine blade disk form a two-stage hollow turbine blade disk.

[0008] Furthermore, the first hollow turbine blades are evenly distributed around the outer circumference of the first circular ring, and the second hollow turbine blades are evenly distributed around the outer circumference of the third circular ring, and there are 30 first hollow turbine blades and 30 second hollow turbine blades.

[0009] Furthermore, the fourth circular ring is provided with an outer rear air inlet.

[0010] Furthermore, the third circular ring is provided with an inner rear air inlet.

[0011] Furthermore, the positions of the outer rear air inlet ports and the inner rear air inlet ports correspond one-to-one inside and outside the circumference of the fourth ring and the third ring, and each outer rear air inlet port is connected to a corresponding inner rear air inlet port to form a rear air inlet pipe, and are arranged in an axial array.

[0012] Furthermore, the interstage gas pipeline includes an interstage gas channel outer wall, an interstage gas channel, and an interstage gas channel inner wall.

[0013] Furthermore, the adjustable guide vane mechanism includes a first rotating shaft, a first adjustable guide vane fixedly connected to the first rotating shaft, a second rotating shaft, and a second adjustable guide vane fixedly connected to the second rotating shaft; the first adjustable guide vane and the second adjustable guide vane are each provided with 30 and are arranged in an axial array.

[0014] Beneficial effects: Compared with the prior art, the present invention has the following significant effects: the use of a double-sided centrifugal compressor improves the air intake efficiency of the generator, and the compressor air is used to cool the turbine blades, ensuring the service life of the hollow turbine blades; by arranging adjustable guide vanes at the combustion chamber outlet and the two-stage hollow turbine blade disk inlet, the gas flow direction is adjusted to make the flow field distribution uniform, and the turbine power generation output response can be improved; the use of a two-stage hollow turbine blade disk fully utilizes the high-temperature gas and improves the thermal efficiency; by arranging coil windings between the two-stage hollow turbine blade disks, efficient energy conversion is achieved, which has environmental benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the structure of the present invention.

[0016] Figure 2 The schematic diagram of the structure of the double-sided compound turbine mechanism of the present invention is

[0017] Figure 3 This is a schematic diagram of the coil winding position of the present invention.

[0018] Figure 4 It is a schematic diagram of the cooperation between the two-stage hollow turbine blade disk and the high-pressure gas according to the present invention.

[0019] Figure 5 It is a schematic diagram of the AA section of the present invention.

[0020] Figure 6 Schematic diagram of gas flow according to the present invention.

[0021] Figure 7 It is a schematic diagram of the BB cross section of the single-sided turbine mechanism of the present invention.

[0022] Figure 8 It is a schematic diagram of the structure of the adjustable guide vane mechanism of the present invention.

[0023] Fig. 9 It is a cross-sectional schematic diagram of the first servo mechanism CC of the present invention.

[0024] Fig.10 It is an enlarged schematic diagram of the first servo mechanism structure of the present invention.

[0025] Fig.11 It is an enlarged schematic diagram of the second servo mechanism structure of the present invention. DETAILED DESCRIPTION

[0026] The present invention discloses a double-sided compound turbine generator with adjustable guide vanes. Figures 1 to 11As shown, the double-sided compound turbine generator with adjustable guide vanes provided by the present invention is further described in detail below: the double-sided compound turbine generator with adjustable guide vanes includes a double-sided compound turbine mechanism, a coil winding 7 sleeved on the double-sided compound turbine mechanism, an interstage gas pipeline sleeved on the coil winding 7, an annular combustion chamber 12 connected to the interstage gas pipeline, a gas transmission channel 11 sleeved on the interstage gas pipeline, and an adjustable guide vane mechanism provided at the inlet of the two-stage hollow turbine blade disk. The double-sided compound turbine mechanism includes a front fairing 6, a first centrifugal compressor 1 connected to the front fairing 6, a first ring 3 connected to the outer periphery of the first centrifugal compressor 1, a first hollow turbine blade 8 connected to the outer periphery of the first ring 3, a second ring 23 connected to the first hollow turbine blade 8, a rear fairing 9, a connecting shaft 5 between the front fairing 6 and the rear fairing 9, a second centrifugal compressor 27 connected to the rear fairing 9, a third ring 24 connected to the outer periphery of the second centrifugal compressor 27, a second hollow turbine blade 26 connected to the outer periphery of the third ring 24, and a fourth ring 25 connected to the outer periphery of the second hollow turbine blade 26. The front fairing 6, the connecting shaft 5, and the rear fairing 9 are coaxially connected in sequence; and the coil winding 7 is sleeved on the outer periphery of the connecting shaft 5. One end of the gas transmission channel 11 is connected to the annular combustion chamber 12, and the other end is connected to the second hollow turbine blade 26; the annular combustion chamber 12 is also connected to the first hollow turbine blade 8, and the annular combustion chamber 12 includes a combustion chamber inner wall 46 and a combustion chamber inner wall 45. The first circular ring 3, the second circular ring 23 and the first hollow turbine blade 8 form a first hollow turbine blade disk 28; the third circular ring 24, the fourth circular ring 25 and the second hollow turbine blade 26 form a second hollow turbine blade disk 29, and are seamlessly fixed in sequence, and the four circular rings play a sealing role; and the first hollow turbine blade disk 28 and the second hollow turbine blade disk 29 form a two-stage hollow turbine blade disk 2. The first hollow turbine blade 8 is evenly distributed around the outer circumference of the first circular ring 3, and the second hollow turbine blade 26 is evenly distributed around the outer circumference of the third circular ring 24, and there are 30 first hollow turbine blades 8 and second hollow turbine blades 26. The fourth circular ring 25 is provided with an outer rear air inlet 4, and the third circular ring 24 is provided with an inner rear air inlet 30. The positions of the outer rear air inlet 4 and the inner rear air inlet 30 correspond to each other in the circumferential direction of the fourth circular ring 25 and the third circular ring 24. Each outer rear air inlet 4 is connected to a corresponding inner rear air inlet 30 to form a rear air inlet pipe 10. The cross-sectional shape of the rear air inlet pipe 10 is elliptical and arranged in an axial array. The interstage gas pipeline includes an interstage gas channel outer wall 36, an interstage gas channel 38, an interstage gas channel inner wall 37, and an exhaust channel 39 arranged at the tail, which are arranged sequentially from the central axis to the outside.The adjustable guide vane mechanism includes a first rotating shaft 13, a first adjustable guide vane 16 fixedly connected to the first rotating shaft 13, a first active rocker arm 40 fixedly connected to the first rotating shaft 13, a first servo motor seat 21 fixedly connected to the inner wall 46 of the combustion chamber, a first servo motor 17 connected to the first servo motor seat 21 by screws, a first output rocker arm 19 fixedly connected to the first servo motor 17, a second rotating shaft 31, a second adjustable guide vane 33 fixedly connected to the second rotating shaft 31, a second active rocker arm 43 fixedly connected to the second rotating shaft 31, a second servo motor seat 47 fixedly connected to the outer wall 36 of the interstage gas channel, a second servo motor 34 connected to the second motor seat 47 by bolts, and a second output rocker arm 42 fixedly connected to the second servo motor 34; wherein the first active passive rocker arm 40 and the first passive rocker arm 41 are connected to the first adjustable guide vane 16. One to one, the second main passive rocker arm 43 and the second passive rocker arm 44 correspond to the second adjustable guide vane 33, and are arranged in an axial array; the first adjustable guide vane 16 and the second adjustable guide vane 32 are each provided with 30, the first main rocker arm 40 is provided with 1, and the first passive rocker arm 41 is provided with 29; the second main rocker arm 43 is provided with 1, and the second passive rocker arm 44 is provided with 29; the minimum distance between the trailing edge of the first adjustable guide vane 16 and the leading edge of the first hollow turbine blade 8 is one-fifth of the blade chord length; the minimum distance between the trailing edge of the second adjustable guide vane 33 and the leading edge of the second hollow turbine blade 26 is one-fifth of the blade chord length; the first main rocker arm 40 is connected to the first passive rocker arm 41 through the first adjusting ring 14, and the second main rocker arm 43 is connected to the second passive rocker arm 44 through the second adjusting ring 32. The first motor output shaft 22 is fixedly connected to the first output rocker arm 19, and the second motor output shaft 48 is fixedly connected to the second output rocker arm 42; the first servo mechanism is arranged in the compartment 20 of the inner wall 46 of the combustion chamber, and the second servo mechanism is arranged in the interlayer 49 between the inner wall 46 of the combustion chamber and the outer wall 36 of the interstage gas channel. The first servo motor 17 drives the first motor output shaft 22 to rotate, and the output shaft drives the first output rocker arm 19. The front end of the rocker arm is provided with a convex shaft, which is engaged with the straight groove on the first active rocker arm 40, so that the first output rocker arm 19 and the first active rocker arm 40 swing in the same direction, thereby driving the adjustment ring 14, and the adjustment ring drives the first passive rocker arm 41 to swing, further driving the corresponding first rotating shaft 13 to rotate, thereby driving the rotation of the corresponding first adjustable guide vane 16, and the actuation principle of the second servo mechanism is the same as that of the first servo mechanism. The rotation of the first adjustable guide vane 16 and the second adjustable guide vane 33 can rectify the gas so that its good and uniform flow field distribution is further improved, and the airflow direction is adjusted, thereby adjusting the turbine speed and output power.

[0027] The working principle of the present invention is as follows: the first centrifugal compressor 1 and the second centrifugal compressor 27 form a double-sided centrifugal compressor, the first centrifugal compressor 1 directly inhales air, and the second centrifugal compressor 27 inhales air from the rear intake pipe 10. The inhaled gas is pressurized by the double-sided centrifugal compressor, and the high-pressure gas formed flows through the trailing edge of the double-sided centrifugal compressor and enters the hollow turbine blades, thereby improving the intake efficiency of the generator. The servo motor drives the motor output shaft and drives the output rocker arm, so that the active rocker arm rotates and drives the adjustment ring to rotate, and then the adjustment ring drives the passive rocker arm, and the active and passive rockers are fixedly connected to the corresponding adjustable guide vanes; the combustion gas discharged from the annular combustion chamber 12 is rectified by the rotation of the adjustable guide vanes, so that its good uniform flow field distribution can be further improved, and the airflow direction can be adjusted, thereby adjusting the turbine speed and output power. The high-pressure gas passes through the combustion chamber inlet 15 and enters the annular combustion chamber 12 to burn and generate high-temperature and high-pressure combustion gas; the high-temperature and high-pressure combustion gas impacts the two-stage hollow turbine blade disk 2, making full use of the high-temperature combustion gas and improving thermal efficiency. Among them, the high-temperature combustion gas contacts the outer wall of the hollow turbine blade to do work, and the high-pressure gas contacts the inner wall of the blade. The two streams of gas perform convection cooling, which prolongs the service life of the blade and ensures the working condition of the blade. The high-temperature combustion gas drives the output shaft of the two-stage hollow turbine blade disk to do work and drives the coil winding 7 on the connecting shaft 5 to generate electricity. After the combustion gas drives the turbine to do work, it is directly discharged along the axial direction to achieve thermoelectric energy conversion, which has environmental benefits and improves the supercharging efficiency and energy utilization efficiency.

Claims

1. A double-sided compound turbine generator with adjustable guide vanes, characterized in that: The invention comprises a double-sided compound turbine mechanism, a coil winding (7) sleeved on the double-sided compound turbine mechanism, an interstage gas pipeline sleeved on the coil winding (7), an annular combustion chamber (12) connected to the interstage gas pipeline, a gas transmission channel (11) sleeved on the interstage gas pipeline, and an adjustable guide vane mechanism; the double-sided compound turbine mechanism comprises a front fairing (6), a first centrifugal compressor (1) connected to the front fairing (6), a first circular ring (3) connected to the outer periphery of the first centrifugal compressor (1), a first hollow turbine blade (8) connected to the outer periphery of the first circular ring (3), a second circular ring (23) connected to the first hollow turbine blade (8), a rear fairing (9), and a plurality of hollow turbine blades (23) located between the front fairing (6) and the rear fairing. (9), a connecting shaft (5) between the front fairing (6), a second centrifugal compressor (27) connected to the rear fairing (9), a third ring (24) connected to the outer periphery of the second centrifugal compressor (27), a second hollow turbine blade (26) connected to the outer periphery of the third ring (24), and a fourth ring (25) connected to the outer periphery of the second hollow turbine blade (26); the front fairing (6), the connecting shaft (5), and the rear fairing (9) are coaxially connected in sequence; the coil winding (7) is sleeved on the outer periphery of the connecting shaft (5); one end of the air delivery channel (11) is connected to the annular combustion chamber (12), and the other end is connected to the second hollow turbine blade (26); the annular combustion chamber (12) is also connected to the first hollow turbine blade (8).

2. The double-sided compound turbine generator with adjustable guide vanes according to claim 1, characterized in that: The first circular ring (3), the second circular ring (23) and the first hollow turbine blade (8) form a first hollow turbine blade disk (28).

3. The double-sided compound turbine generator with adjustable guide vanes according to claim 1, characterized in that: The third circular ring (24), the fourth circular ring (25) and the second hollow turbine blade (26) form a second hollow turbine blade disk (29).

4. The double-sided compound turbine generator with adjustable guide vanes according to claim 2 or 3, characterized in that: The first hollow turbine blade disk (28) and the second hollow turbine blade disk (29) form a two-stage hollow turbine blade disk (2).

5. The double-sided compound turbine generator with adjustable guide vanes according to claim 1, characterized in that: The first hollow turbine blades (8) are evenly distributed around the outer circumference of the first circular ring (3), and the second hollow turbine blades (26) are evenly distributed around the outer circumference of the third circular ring (24), and there are 30 first hollow turbine blades (8) and 30 second hollow turbine blades (26).

6. The double-sided compound turbine generator with adjustable guide vanes according to claim 1, characterized in that: The fourth circular ring (25) is provided with an outer rear air inlet (4).

7. The double-sided compound turbine generator with adjustable guide vanes according to claim 6, characterized in that: The third circular ring (24) is provided with an inner rear air inlet (30).

8. The double-sided compound turbine generator with adjustable guide vanes according to claim 7, characterized in that: The positions of the outer rear air inlet (4) and the inner rear air inlet (30) correspond to each other one by one in the circumferential direction of the fourth circular ring (25) and the third circular ring (24), and each outer rear air inlet (4) is connected to a corresponding inner rear air inlet (30) to form a rear air inlet pipe (10), and are arranged in an axial array.

9. The double-sided compound turbine generator with adjustable guide vanes according to claim 1, characterized in that: The interstage gas pipeline comprises an interstage gas channel outer wall (36), an interstage gas channel (38), and an interstage gas channel inner wall (37).

10. The double-sided compound turbine generator with adjustable guide vanes according to claim 9, characterized in that: The adjustable guide vane mechanism comprises a first rotating shaft (13), a first adjustable guide vane (16) fixedly connected to the first rotating shaft (13), a second rotating shaft (31), and a second adjustable guide vane (33) fixedly connected to the second rotating shaft (31); 30 first adjustable guide vanes (16) and 30 second adjustable guide vanes (33) are provided and arranged in an axial array.

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