Turbine power generation device and aviation power system

Abstract

The invention belongs to the technical field of aircraft power devices, and discloses a turbine power generation device and an aviation power system.The turbine power generation device comprises a first fluid director, a second fluid director, a third fluid director and a fourth fluid director, a turbine rotor having a first blade group and a second blade group, the first blade group being attached to the outer periphery of the second blade group; the turbine rotor is mounted between the first fluid director and the second fluid director; wherein the first flow channel is communicated to the first blade group, the second flow channel is communicated to the second blade group, the first blade group is designed to be used for driving a turbine rotor to rotate, the second blade group is designed to be used for extracting gas in the cavity, and the turbine rotor drives a power generator to generate power. The invention aims to provide a turbine power generation device and an aviation power system, and provides a power system capable of prolonging the voyage of an aircraft.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft power devices, and particularly relates to a turbine power generation device and an aviation power system. Background Art

[0002] Low-altitude economy is a field with broad development prospects and depth currently and in the future.

[0003] In the field of pure electric unmanned aircraft, the power source is a battery pack. Constrained by the existing battery technology, the endurance time of pure electric unmanned aircraft is relatively short and they cannot work for a long time. At the same time, considering the safety factors of the aircraft, a certain margin needs to be left for the battery, resulting in an even shorter actual endurance time. Even if the battery technology is upgraded in the future, it is difficult for pure electric unmanned aircraft to meet the long endurance requirements under the new demands.

[0004] For the above reasons, there is an urgent need for a power generation device to directly supply power to the on-board drive motor of the unmanned aircraft or to charge the battery of the unmanned aircraft for range extension, so as to meet the longer endurance requirements of the unmanned aircraft. Summary of the Invention

[0005] Aiming at the above problems, the technical object of the present invention is to provide a turbine power generation device and an aviation power system.

[0006] The present invention is realized through the following technical solutions:

[0007] On the one hand, the present application provides a turbine power generation device, including:

[0008] A first deflector having a first flow path for deflecting high-temperature gas. A cavity is formed inside the first deflector, and the cavity communicates with the outside of the first deflector through a second flow path;

[0009] A turbine rotor is installed at the fluid outlet of the first deflector, and has a first blade group and a second blade group. The first blade group is installed on the outer periphery of the second blade group;

[0010] A second deflector, and the turbine rotor is installed between the first deflector and the second deflector;

[0011] Wherein, the first flow path communicates with the first blade group, the second flow path communicates with the second blade group. The first blade group is designed to drive the turbine rotor to rotate, the second blade group is designed to extract the gas in the cavity, and the turbine rotor drives the generator to generate electricity.

[0012] In some embodiments, the second deflector is formed with a third flow path and a fourth flow path that communicate with the flow paths of the first blade group and the second blade group respectively.

[0013] In some embodiments, the interior of the generator has a heat dissipation flow channel, and the second deflector is provided with a plurality of fifth flow channels communicating with the outside thereof, and the fifth flow channels communicate with the heat dissipation flow channel.

[0014] In some embodiments, a first sleeve is provided outside the generator, and a fluid channel is formed between the first sleeve and the outer shell of the generator.

[0015] In some embodiments, the air inlet end of the first deflector is connected to the exhaust end of the gas generator.

[0016] In some embodiments, the cavity communicates with the outside of the first deflector through a plurality of tubular structures passing through the first flow channel.

[0017] In some embodiments, the first deflector, the turbine rotor, the second deflector and the generator are connected in sequence, and the first flow channel and the third flow channel are designed to be arranged along the axial direction.

[0018] In some embodiments, one end of the generator close to the second deflector communicates the interior of the generator with the outside of the second deflector through a fifth flow channel.

[0019] In some embodiments, the generator is coaxially installed with the turbine rotor.

[0020] In some embodiments, an air extraction impeller is installed on the rotating shaft of the generator.

[0021] In some embodiments, a second sleeve is further sleeved outside the first sleeve, and a fluid channel communicating with the flow channel where the second blade group is located is formed between the second sleeve and the first sleeve.

[0022] In some embodiments, a fuel pipeline is connected to the fluid channel between the first sleeve and the outer shell of the generator, and the fuel pipeline passes through the fifth flow channel and is connected to the outside.

[0023] In some embodiments, a sixth flow channel communicating with the exhaust side of the second blade group is formed in the pipe wall of the fifth flow channel, and the sixth flow channel communicates with the outside of the second deflector.

[0024] In some embodiments, the air extraction impeller is installed at one end far from the second deflector.

[0025] On the other hand, the present invention provides an aero power system, including the turbine power generation device, and the turbine power generation device supplies power to the connected aero motor and / or storage battery.

[0026] The turbine power generation device and aviation power system proposed by the present invention can improve the power of the overall power system compared with the prior art. Through the unique and excellent design of the turbine power generation device, the efficiency of the power system can be improved, the endurance of the aircraft can be increased, and the heat dissipation system and thermal shielding system of the generator ensure the normal operation of the generator, ensuring that the turbine power generation device meets the power generation requirements of the aviation power system. Brief Description of the Drawings

[0027] Figure 1 is a schematic diagram of the overall structure of the turbine power generation device of the present application;

[0028] Figure 2 is the present application Figure 1 Schematic cross-sectional structure diagram in the A-A direction;

[0029] Figure 3 is the present application Figure 1 Left view;

[0030] Figure 4 is the present application Figure 3 Schematic cross-sectional structure diagram in the B-B direction

[0031] Figure 5 is a schematic diagram of a partial cross-sectional structure of the present application;

[0032] Figure 6 is a schematic diagram of the structure of the turbine rotor of the present application;

[0033] Figure 7 is a schematic diagram of the structure of the first sleeve. Detailed Description of the Invention

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments in conjunction with the accompanying drawings in the embodiments of the present invention. The following embodiments are used to illustrate the present invention but are not used to limit the scope of the present invention.

[0035] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is 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 construed as a limitation to the present invention.

[0036] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installation", "connection", and "linkage" 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. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0037] The present invention will be described in detail below with reference to the accompanying drawings.

[0038] On the one hand, the present invention provides a turbine power generation device, as Figures 1-7 shown, Figure 2 and Figure 3 , Figure 4 is a sectional structure diagram of the present invention. The turbine power generation device includes:

[0039] The first deflector 3 has a first flow channel 31 for deflecting high-temperature gas. A cavity 33 is formed in the first deflector 3, and the cavity 33 communicates with the outside of the first deflector 3 through a second flow channel 32;

[0040] The turbine rotor 5 is installed at the fluid outlet of the first deflector 3 and has a first blade group 51 and a second blade group 52. The first blade group 51 is installed on the outer periphery of the second blade group 52. The second blade group 52 is evenly installed on the outer periphery of the carrier disk 54. A separating ring 53 that separates the first blade group 51 and the second blade group 52 is installed on the outer periphery of the second blade group 52, as Figure 6 shown.

[0041] The second deflector 6, and the turbine rotor 5 is installed between the first deflector 3 and the second deflector 6;

[0042] Among them, the first flow channel 31 communicates with the first blade group 51, the second flow channel 32 communicates with the second blade group 52. The first blade group 51 is designed to drive the turbine rotor 5 to rotate. The second blade group 52 is designed to extract the gas in the cavity 33 and make the extracted gas flow toward the generator 7 side, and the turbine rotor 5 drives the generator 7 to generate electricity.

[0043] Specifically, the intake end of the first deflector 3 is connected to the exhaust end of the gas generator 1. The specific connection method can be that the first deflector 3 is connected to the tail nozzle 2 of the gas generator 1, or the first deflector 3 and the engine tail nozzle 2 are installed as an integral structure. The first flow channel 31 of the first deflector 3 is used to guide the high-temperature and high-pressure gas generated by the gas generator 1 to the flow channel where the first set of blades 51 of the turbine rotor 5 are located. By doing work on the first set of blades 51 with the high-temperature and high-pressure gas, the first set of blades 51 are driven by the airflow ejected from the gas generator, and the first set of blades 51 drive the entire turbine rotor 5 to rotate. When the turbine rotor 5 rotates, the second blade group 52 it has is also driven, and the second blade group 52 thus enables the airflow to flow toward the generator 7 side through the flow channel of the second deflector 6. The turbine rotor 5 and the generator 7 are coaxially designed, so that the turbine rotor 5 can directly drive the rotor 72 of the generator 7 to rotate. The rotor 72 cooperates with the generator stator to generate electricity, and the second deflector 6 deflects the gas discharged from the turbine rotor 5 respectively. The first deflector 3, the turbine rotor 5, the second deflector 6 and the generator 7 are connected. The first flow channel 31 and the third flow channel 61 are designed to be arranged in the axial direction, so as to provide thrust for the gas discharged from the third flow channel 61. Therefore, compared with the existing turbine power generation device, the present invention can provide additional thrust for the aircraft. It should be known that the intake of the turbine generator 1 enters from a certain direction. In order to better provide intake for the turbine generator and to better form thrust, the exhaust direction of the third flow channel 61 is the same as the intake direction of the turbine generator 1.

[0044] In one embodiment, the rotating shafts of the turbine rotor 5 and the generator 7 adopt self-lubricating ceramic bearings, which reduce the lubrication system and can improve the service life of the bearings.

[0045] In some embodiments, the first deflector 3 has a cylindrical structure, and the cavity 33 is formed inside the first flow channel 31, that is, the first flow channel 31 surrounds the outer periphery of the cavity 33. The cavity 33 can have various shapes, such as a conical shape, etc., and is usually set as a hemispherical or semi-elliptical shape to form a certain cavity structure to isolate high-temperature gas and at the same time accommodate external air.

[0046] In some embodiments, the second deflector 6 is formed with a third flow channel 61 and a fourth flow channel 62 that are respectively in fluid communication with the flow channels of the first blade group 51 and the second blade group 52. Among them, both the third flow channel 61 and the fourth flow channel 62 are annular structures. Correspondingly to the first deflector 3, the third flow channel 61 is provided on the outer periphery of the fourth flow channel 62. The third flow channel 61 is used to discharge the high-temperature and high-pressure gas generated by the turbine rotor 5, and the fourth flow channel 62 is used to discharge the gas extracted by the second group of blades 52 of the turbine rotor 5. The gas extracted by the second group of blades 52 is introduced from the air, and its low temperature can isolate the high-temperature gas discharged from the third flow channel 61, thereby protecting the generator 7 and forming a heat insulation barrier.

[0047] In some embodiments, a first sleeve 8 is sleeved outside the generator 7, and a fluid channel is formed between the first sleeve 8 and the outer shell of the generator. A second sleeve 9 is further sleeved outside the first sleeve 8, and a fluid channel in communication with the flow channel where the second blade group 52 is located is formed between the second sleeve 9 and the first sleeve 8. The first sleeve 8 has two fluid ports 81 for liquid inlet and liquid discharge respectively, and is arranged as shown in Figure 7 shown.

[0048] Specifically, both ends of the first sleeve 8 are closed with the two ends of the outer shell of the generator, and only the inlet and outlet are left respectively. In order to better cool and insulate the generator 7 and prevent the generator from getting too hot, the fluid channel between the first sleeve 8 and the outer shell of the generator 7 is connected to a fuel pipeline 10. Fuel enters the fluid channel between the first sleeve 8 and the outer shell of the generator through the fuel pipeline 10, and is discharged after heat exchange, which can cool the generator 7 and also preheat the fuel. The preheated fuel can be transported to the gas generator for combustion. The flow channel formed between the second sleeve 9 and the first sleeve 8 is along the axial direction of the generator 7. The second sleeve 9 and the first sleeve 8 have an open structure at both ends, allowing gas to flow through. The fluid channel formed between the second sleeve 9 and the first sleeve 8 enables the gas extracted by the second blade group 52 to pass through the fluid channel between the second sleeve 9 and the first sleeve 8 from the side of the generator 7 close to the second deflector 6 and be discharged from the side away from the second deflector 6. Therefore, a protective barrier can be formed for the generator 7.

[0049] To further cool the generator 7, in some embodiments, the interior of the generator 7 is provided with a heat dissipation flow channel 71, which is usually arranged between the stator 73 and the rotor 72 of the generator 7. Alternatively, several flow channels can be provided on the stator 72 as the heat dissipation flow channel 71. The second deflector 6 is provided with several fifth flow channels 63 communicating with its exterior, and the fifth flow channels 63 communicate with the heat dissipation flow channel 71. The number of the fifth flow channels 63 is set as required, with at least one, so that air can be introduced into the interior of the generator 7 through the fifth flow channels 63 for cooling. In a preferred embodiment, one end of the generator 7 close to the second deflector 6 communicates the interior of the generator with the exterior of the second deflector 6 through the fifth flow channels 63. Further, to accelerate the flow velocity of the air flow in the heat dissipation flow channel 71 inside the generator 7, an air extraction impeller 11 is installed on the rotating shaft of the generator 7, which can be installed on one side of the generator rotating shaft close to the second deflector 6. Preferably, the air extraction impeller 11 is installed on the side of the generator rotating shaft away from the second deflector 6, that is, the air extraction impeller 11 is installed at the tail of the generator 7, which is more convenient for installation. The outer periphery of the air extraction impeller 11 is provided with an impeller cover 13, which is integrated with the generator housing / the first sleeve or the impeller cover 13 is installed on the motor housing / the first sleeve. The impeller cover 13 should be cylindrical so that the air flow can flow along its axial direction.

[0050] In some embodiments, the cavity 33 communicates with the exterior of the first deflector 3 through several tubular structures passing through the first flow channel 31, so as to introduce air from the exterior of the first deflector 3. Specifically, the second flow channel 32 can pass through the first flow channel 31 to communicate with the exterior from the outer shell of the first deflector 3, and the second flow channel 32 can also pass through the tail nozzle 2 of the gas generator to communicate with the exterior. Here, the flow channel in the part of the tail nozzle 2 also belongs to the first flow channel 31, and the same applies when the part of the tail nozzle 2 of the gas generator and the first deflector 3 are integrated. The cross-section of the second flow channel 32 formed can be elliptical. Generally, the second flow channel 32 is arranged to occupy as little flow space of the first flow channel 31 as possible, so as to minimize the influence on the first flow channel 31.

[0051] In some embodiments, the fuel pipeline 10 is arranged to pass through the middle of the fifth flow channel 63 and connect to the exterior, so as to reduce or avoid the influence of high-temperature gas on the fuel pipeline 10. The fuel pipeline 10 is installed on one side of the first sleeve 8 close to the second deflector 6. There are at least two fuel pipelines 10, which are respectively an oil inlet pipeline and an oil outlet pipeline, and can also be multiple.

[0052] In some embodiments, the direction of the fourth flow channel 62 is arranged along the axial direction of the power generation device so as to communicate with the flow channel formed between the second sleeve 9 and the first sleeve 8. The gas discharged through the second sleeve 9 can also provide a forward thrust, and the gas in the second sleeve 9 can isolate the high-temperature exhaust gas generated by the gas generator.

[0053] In some embodiments, the generator 7 and the turbine rotor 5 are coaxially installed, which can reduce the number of fittings and improve the coaxiality. The rotating shafts 12 of the generator 7 and the turbine rotor 5 are installed in cooperation with the second deflector 6 through bearing seats.

[0054] In some embodiments, a sixth flow channel 631 communicating with the exhaust side of the second blade group 52 is formed in the pipe wall of the fifth flow channel 63. The sixth flow channel 631 communicates with the outside of the second deflector 6, so as to play a heat shielding role for the high-temperature gas flow in the third flow channel 61 and prevent the temperature of the gas flow in the fifth flow channel 63 from being too high. In order to facilitate the flow of the gas in the sixth flow channel 631, a drainage hole 632 is provided in the pipe wall of the fifth flow channel 63.

[0055] In some embodiments, the first deflector 3, the turbine rotor 5, and the second deflector 6 are all integral structures and are formed by 3D printing. While meeting the use functions, the structure of the parts is simplified, the number of parts is reduced, the overall weight is reduced, and the power-to-weight ratio of the equipment is improved. The first deflector 3 includes a guiding body structure, which can be regarded as a turbine stator casing, and also includes stator blades 4. The stator blades 4 are arranged at the outlet part of the first flow channel 31 of the first deflector 3. The integral molding of the second deflector 6 should be understood that the overall structure of the second deflector 6 and the cooling pipeline passing through the second deflector 6, that is, the pipeline of the fifth flow channel 63 and the fuel pipeline 10 are an integral structure with the second deflector 6 and can be regarded as a part of the second deflector 6. The second deflector integrates the functions of the fifth flow channel 63 and the fuel pipeline 10.

[0056] As Figure 5As shown, in the present invention, the high-temperature gas discharged from the gas generator passes through the first flow path 31, does work on the first blade group 51, and then is discharged from the third flow path 61. This fluid route is the high-temperature gas flow path 001. In the present invention, the gas outside the turbo-generator is introduced into the cavity 33 in the first deflector through the second flow path 32. The second blade group 52, which is driven, does work on the gas, so that the gas in the cavity 33 is pressurized and transported to the fourth flow path 62, and further transported to the fluid passage formed between the second sleeve 9 and the first sleeve 8, and then discharged. This flow path is the first cooling flow path 002. In the present invention, the fifth flow path 63 introduces air from outside the turbo-generator, passes through the inside of the generator 7, and is discharged through the air extraction impeller 11. This is the second cooling flow path 003. In the present invention, fuel is introduced from one side through the fuel pipe 10, and through the fluid passage between the first sleeve 8 and the outer shell of the generator 7, it is transported around the motor housing to the oil discharge end of the other fuel pipe 10. This is the third cooling flow path 004.

[0057] On the other hand, the present invention also provides an aero-power system, including the above-mentioned turbo-generator, which supplies power to the connected aero-motor and / or storage battery, so that the turbo-generator, the aero-motor and the storage battery can form an efficient and reliable power propulsion device.

[0058] The above are only the preferred embodiments of the present application, and do not impose any formal restrictions on the present application. Although the present application has been disclosed above with the preferred embodiments, it is not intended to limit the present application. Any person skilled in the art of this patent, without departing from the scope of the technical solution of the present invention, can make some changes or modifications to the above-mentioned technical content to obtain equivalent embodiments with equivalent changes. However, as long as it does not depart from the content of the technical solution of the present application, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application still fall within the scope of the present application.

Claims

1. A turbine power generation device, characterized in that, Comprising: A first deflector (3) having a first flow channel (31) for deflecting high-temperature gas. A cavity (33) is formed inside the first deflector (3), and the cavity (33) communicates with the outside of the first deflector (3) through a second flow channel (32). A turbine rotor (5) having a first blade group (51) and a second blade group (52), and the first blade group (51) is installed on the outer periphery of the second blade group (52). A second deflector (6), and the turbine rotor (5) is installed between the first deflector (3) and the second deflector (6). Wherein, the first flow channel (31) communicates with the first blade group (51), the second flow channel (32) communicates with the second blade group (52), the first blade group (51) is designed to drive the turbine rotor (5) to rotate, the second blade group (52) is designed to extract the gas in the cavity (33), and the turbine rotor (5) drives the generator (7) to generate electricity.

2. The turbine power generation device according to claim 1, characterized in that, The second deflector (6) forms a third flow channel (61) and a fourth flow channel (62) that communicate with the flow channels of the first blade group (51) and the second blade group (52) respectively.

3. The turbine power generation device according to claim 1, characterized in that The generator (7) has a heat dissipation flow channel (71) inside, and the second deflector (6) is provided with a plurality of fifth flow channels (63) communicating with the outside thereof, and the fifth flow channels (63) communicate with the heat dissipation flow channel (71).

4. The turbine power generation device according to claim 1 or 2 or 3, characterized in that, A first sleeve (8) is sleeved outside the generator (7), and a fluid channel is formed between the first sleeve (8) and the outer shell of the generator.

5. The turbine power generation device according to claim 1, wherein, The intake end of the first deflector (3) is connected to the exhaust end of the gas generator (1).

6. The turbine power generation device according to claim 1, wherein, The cavity (33) communicates with the outside of the first deflector (3) through a plurality of tubular structures passing through the first flow channel (31).

7. The turbine power generation device according to claim 2, characterized in that The first deflector (3), the turbine rotor (5), the second deflector (6) and the generator (7) are connected in sequence, and the first flow channel (31) and the third flow channel (61) are designed to be arranged in the axial direction.

8. The turbine power generation device according to claim 3, characterized in that, One end of the generator close to the second deflector (6) communicates the inside of the generator with the outside of the second deflector (6) through the fifth flow channel (63).

9. The turbine power generation device according to claim 1 or 2 or 3, characterized in that, The generator is coaxially installed with the turbine rotor (5).

10. The turbine power generation device according to claim 3, characterized in that, An air extraction impeller (11) is installed on the rotating shaft of the generator (7).

11. The turbine power generation device according to claim 4, wherein, A second sleeve (9) is further sleeved outside the first sleeve (8), and a fluid channel communicating with the flow channel where the second blade group (52) is located is formed between the second sleeve (9) and the first sleeve (8).

12. The turbine power generation device according to claim 4, characterized in that, A fuel pipeline (10) is connected to the fluid channel between the first sleeve (8) and the outer shell of the generator, and the fuel pipeline (10) passes through the fifth flow channel (63) and is connected to the outside.

13. The turbine power generation device according to claim 3 or 8, characterized in that, A sixth flow channel (631) communicating with the exhaust side of the second blade group (52) is formed in the pipe wall of the fifth flow channel (63), and the sixth flow channel (631) communicates with the outside of the second deflector (6).

14. The turbine power generation device according to claim 10, characterized in that, The air extraction impeller (11) is installed at the end far from the second deflector (6).

15. An aviation power system, characterized in that, A turbine power generation device including any one of claims 1-14, the turbine power generation device supplying power to an aviation electric machine and / or a storage battery connected thereto.

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