Turbine power generation device and aviation power equipment
By designing a turbine power generation device, which uses high-temperature and high-pressure gas to drive the turbine rotor to rotate, directly powering the aircraft motor or battery, the problem of short endurance of unmanned aerial vehicles is solved, achieving a more efficient power system and a longer endurance.
Patent Information
- Application Number
- CN202520359061.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-04
- Publication Date
- 2026-02-10
- Estimated Expiration
- 2035-03-04
AI Technical Summary
Existing pure electric unmanned aerial vehicles have a short flight time, which cannot meet the needs of long-term operation, and battery technology upgrades are also difficult to solve this problem.
Design a turbine power generation device, including a first guide vane, a turbine rotor, a second guide vane, and a generator. The turbine rotor is driven to rotate by high-temperature and high-pressure gas, directly powering the aircraft motor or battery. Combined with a heat dissipation channel and a heat shielding system, the efficiency of the power system and the range are improved.
It improves the efficiency and endurance of the aircraft's power system, ensures the generator operates normally, provides additional thrust, and extends flight time.
Smart Images
Figure CN223894267U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the technical field of aircraft power devices, and specifically relates to a turbine power generation device and aviation power equipment. Background Technology
[0002] The low-altitude economy is a field with broad development prospects and depth, both now and in the future. Unmanned aerial vehicles (UAVs) have significant strategic importance for economic development and national security. Especially in the military field, UAV reconnaissance, strike, integrated reconnaissance and strike capabilities, and swarm attacks will become the mainstream forms of future warfare.
[0003] In the field of pure electric unmanned aerial vehicles (UAVs), the power source is the battery pack. Due to the limitations of existing battery technology, pure electric UAVs have a short flight time and cannot work for a long time. At the same time, considering the safety factors of the aircraft, the battery needs to have a certain margin, which leads to a shorter actual flight time. Even if battery technology is upgraded in the future, pure electric UAVs will still find it difficult to meet the long flight time requirements under the new demands.
[0004] For the reasons mentioned above, there is an urgent need for a power generation device that can directly power the onboard drive motor of the drone or extend the range of the drone's battery to meet the requirement of longer flight time for the drone. Utility Model Content
[0005] In view of the above-mentioned problems, the technical objective of this utility model is to provide a turbine power generation device and an aviation power equipment.
[0006] This utility model is achieved through the following technical solution:
[0007] On the one hand, this utility model provides a turbine power generation device, comprising:
[0008] A first flow guide has a first flow channel arranged along its axial direction and a cavity formed therein, the cavity being connected to the outside of the first flow guide through a second flow channel;
[0009] The turbine rotor has a first blade group and a second blade group, wherein the first blade group is mounted on the outer periphery of the second blade group;
[0010] The second guide vane is provided, and the turbine rotor is installed between the first guide vane and the second guide vane.
[0011] The first flow channel is connected to the first blade group, and the second flow channel is connected to the second blade group. The first blade group is designed to drive the turbine rotor to rotate, and the second blade group is designed to extract the gas in the cavity. The turbine rotor drives the generator to generate electricity, and the generator has a heat dissipation flow channel inside.
[0012] In some embodiments, the second flow guide has a third flow channel and a fourth flow channel respectively communicating with the flow channels of the first blade group and the second blade group.
[0013] In some embodiments, the second flow guide is provided with a plurality of fifth flow channels communicating with the outside of it, the fifth flow channels being connected to the heat dissipation flow channels.
[0014] In some embodiments, the generator housing is provided with a first sleeve, and a fluid channel is formed between the first sleeve and the generator housing.
[0015] In some embodiments, the inlet end of the first flow guide is connected to the exhaust end of the gas generator.
[0016] In some embodiments, the cavity is connected to the outside of the first flow guide through a plurality of tubular structures passing through the first flow channel.
[0017] In some embodiments, the first flow guide, the turbine rotor, the second flow guide, and the generator are connected in sequence, and the third flow channel is designed to be arranged along the axial direction.
[0018] In some embodiments, the end of the generator near the second guide tube connects the interior of the generator to the exterior of the second guide tube via a fifth flow channel.
[0019] In some embodiments, the generator is mounted coaxially with the turbine rotor.
[0020] In some embodiments, an exhaust impeller is mounted on the 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 line is connected to the fluid passage between the first sleeve and the housing of the generator, the fuel line passing through the fifth flow channel and connecting to the outside.
[0023] In some embodiments, a sixth flow channel is formed within the wall of the fifth flow channel, communicating with the exhaust side of the second blade group, and the sixth flow channel is communicating with the outside of the second guide.
[0024] In some embodiments, the exhaust impeller is mounted at the end away from the second guide vane.
[0025] On the other hand, this utility model provides an aviation power equipment, including a turbine generator, which supplies power to the connected aircraft motor and / or battery.
[0026] The turbine generator and aviation power equipment proposed in this utility model can improve the overall power of the power system compared with the prior art. Through the unique and excellent design of the turbine generator, the efficiency of the power system can be improved, the range of the aircraft can be increased, and the heat dissipation system and heat shielding system of the generator can ensure the normal operation of the generator and ensure that the turbine generator meets the power generation requirements of the aviation power equipment. Attached Figure Description
[0027] Figure 1 This is a schematic diagram of the overall structure of the turbine power generation device of this application;
[0028] Figure 2 This application Figure 1 Schematic diagram of the cross-sectional structure along the AA direction;
[0029] Figure 3 This application Figure 1 The left view;
[0030] Figure 4 This application Figure 3 Cross-sectional structure diagram in the middle BB direction
[0031] Figure 5 This is a partial cross-sectional structural diagram of this application;
[0032] Figure 6 This is a schematic diagram of the turbine rotor structure of this application;
[0033] Figure 7 This is a schematic diagram of the structure of the first sleeve in this application. Detailed Implementation
[0034] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings. The following embodiments are used to illustrate this utility model, but are not intended to limit the scope of this utility model.
[0035] In the description of this utility model, it should be noted that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "inner", and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.
[0036] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.
[0037] The present invention will now be described in detail with reference to the accompanying drawings.
[0038] On the one hand, this utility model provides a turbine power generation device, such as Figures 1-7 As shown, Figure 2 and Figure 3 , Figure 4 This is a cross-sectional view of the present invention. The turbine power generation device includes:
[0039] The first flow guide 3 has a first flow channel 31 for guiding high-temperature gas flow, and a cavity 33 is formed inside the first flow guide 3. The cavity 33 is connected to the outside of the first flow guide 3 through a second flow channel 32.
[0040] The turbine rotor 5, installed at the fluid outlet of the first guide vane 3, 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, and the second blade group 52 is evenly installed on the outer periphery of the support plate 54. A partition ring 53 is installed on the outer periphery of the second blade group 52 to separate the first blade group 51 and the second blade group 52. Figure 6 As shown.
[0041] The second guide vane 6, wherein the turbine rotor 5 is installed between the first guide vane 3 and the second guide vane 6;
[0042] The first flow channel 31 is connected to the first blade group 51, and the second flow channel 32 is connected to the second blade group 52. The first blade group 51 is designed to drive the turbine rotor 5 to rotate, and the second blade group 52 is designed to extract the gas in the cavity 33 and make the extracted gas flow towards the generator 7. The turbine rotor 5 drives the generator 7 to generate electricity.
[0043] Specifically, the inlet end of the first guide vane 3 is connected to the exhaust end of the gas generator 1. Specifically, the first guide vane 3 can be connected to the exhaust nozzle 2 of the gas generator 1, or the first guide vane 3 and the exhaust nozzle 2 can be installed as a single unit. The first flow channel 31 of the first guide vane 3 guides the high-temperature, 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 is located. The high-temperature, high-pressure gas performs work on the first set of blades 51, causing the first set of blades 51 to be driven by the airflow ejected from the gas generator. The first set of blades 51 drives the turbine rotor 5 to rotate as a whole. As the turbine rotor 5 rotates, its second set of blades 52 is also driven, allowing the airflow to flow through the flow channel of the second guide vane 6 towards the generator 7. The turbine rotor 5 and the generator 7 are coaxially designed, allowing the turbine rotor 5 to directly drive the rotor 72 of the generator 7 to rotate. The rotor 72 cooperates with the generator stator to generate electricity. The second guide vane 6 guides the gas discharged from the turbine rotor 5. The first guide vane 3, the turbine rotor 5, the second guide vane 6, and the generator 7 are connected. The first flow channel 31 and the third flow channel 61 are designed to be arranged axially so that the gas discharged from the third flow channel 61 can provide thrust. Therefore, compared with existing turbine power generation devices, this invention can provide additional thrust for the aircraft. It should be understood that the turbine generator 1's air intake enters from a certain direction. In order to better provide air intake for the turbine generator and to better generate thrust, the exhaust direction of the third flow channel 61 is consistent with the air intake direction of the turbine generator 1.
[0044] In one embodiment, the turbine rotor 5 and the generator 7 use self-lubricating ceramic bearings, which reduces the need for a lubrication system and improves the bearing life.
[0045] In some embodiments, the first flow guide 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 be of various shapes, such as a cone shape, and is usually set as a hemispherical or semi-ellipsoidal shape to form a certain cavity structure to accommodate gas.
[0046] In some embodiments, the second guide vane 6 has a third flow channel 61 and a fourth flow channel 62 that are respectively connected to the flow channels of the first blade group 51 and the second blade group 52. Both the third flow channel 61 and the fourth flow channel 62 are annular structures. Corresponding to the first guide vane 3, the third flow channel 61 is located on the outer periphery of the fourth flow channel 62. The third flow channel 61 is used to discharge the high-temperature, high-pressure airflow generated by the turbine rotor 5, and the fourth flow channel 62 is used to discharge the gas extracted by the second set of blades 52 of the turbine rotor 5. The gas extracted by the second set of blades 52 is introduced from the air, and its low temperature can isolate the high-temperature gas discharged by the third flow channel 61, thereby protecting the generator 7 and forming a heat insulation barrier.
[0047] In some embodiments, the generator 7 is fitted with a first sleeve 8, and a fluid channel is formed between the first sleeve 8 and the generator housing. A second sleeve 9 is also fitted over the first sleeve 8, and a fluid channel communicating with the flow channel of the second blade assembly 52 is formed between the second sleeve 9 and the first sleeve 8. The first sleeve 8 has two flow ports 81 for liquid inlet and liquid outlet, respectively, which are arranged on the first sleeve 8, such as... Figure 7 As shown.
[0048] Specifically, the first sleeve 8 is closed at both ends to the generator housing, leaving only an inlet and an outlet. To better cool and insulate the generator 7 and prevent overheating, a fuel pipe 10 is connected to the fluid channel between the first sleeve 8 and the generator housing. Fuel enters the fluid channel between the first sleeve 8 and the generator housing through the fuel pipe 10, exchanges heat, and is then discharged. This cools the generator 7 and preheats the fuel, which can then be sent 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 open ends, allowing gas flow. The fluid channel between the second sleeve 9 and the first sleeve 8 allows the gas drawn out by the second blade assembly 52 to pass through the fluid channel between the second sleeve 9 and the first sleeve 8 from the side of the generator 7 closest to the second guide vane 6 and be discharged from the side furthest from the second guide vane 6. Therefore, this forms a protective barrier for the generator 7.
[0049] To further cool the generator 7, in some embodiments, the generator 7 is configured to have a heat dissipation channel 71 inside. The heat dissipation channel 71 is usually located between the stator 73 and the rotor 72 of the generator 7. Alternatively, several channels can be provided on the stator 72 as the heat dissipation channel 71. The second flow guide 6 is provided with several fifth channels 63 that connect to its outside. The fifth channels 63 are connected to the heat dissipation channel 71. The number of fifth channels 63 is set as needed, with at least one. This allows air to be introduced into the generator 7 for cooling through the fifth channels 63. In a preferred embodiment, the end of the generator 7 near the second flow guide 6 connects the inside of the generator to the outside of the second flow guide 6 through the fifth channels 63. Furthermore, to accelerate the airflow speed within the internal heat dissipation channel 71 of the generator 7, an extraction impeller 11 is installed on the shaft of the generator 7. This impeller can be installed on the side of the generator shaft closest to the second guide vane 6, or more preferably, on the side of the generator shaft furthest from the second guide vane 6, i.e., at the tail end of the generator 7, which facilitates installation. An impeller cover 13 is provided on the outer periphery of the extraction impeller 11. The impeller cover 13 is integral with the generator housing / first sleeve, or the impeller cover 13 is installed on the generator housing / first sleeve. The impeller cover 13 should be cylindrical to allow airflow along its axial direction.
[0050] In some embodiments, the cavity 33 communicates with the outside of the first guide vane 3 through several tubular structures passing through the first flow channel 31, thereby introducing air from outside the first guide vane 3. Specifically, the second flow channel 32 can communicate with the outside of the outer shell of the first guide vane 3 through the first flow channel 31, and the second flow channel 32 can also communicate with the outside through the tailpipe 2 of the gas generator. Here, the flow channel in the tailpipe 2 section also belongs to the first flow channel 31, which also applies when the tailpipe 2 section of the gas generator is integrated with the first guide vane 3. The cross-section forming the second flow channel 32 can be elliptical. Generally, the second flow channel 32 should occupy as little flow space as possible in the first flow channel 31 in order to minimize the impact on the first flow channel 31.
[0051] In some embodiments, the fuel line 10 is configured to pass through the middle of the fifth flow channel 63 and connect to the outside, in order to reduce or avoid the influence of high-temperature combustion gas on the fuel line 10. The fuel line 10 is installed on the side of the first sleeve 8 near the second flow guide 6, and there are at least two fuel lines 10, namely an inlet line and an outlet line, or there may be multiple lines.
[0052] In some embodiments, 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 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 mounted, which can reduce the number of components and improve coaxiality. The shaft 12 of the generator 7 and the turbine rotor 5 are installed in conjunction with the second guide vane 6 through bearings.
[0054] In some embodiments, a sixth flow channel 631 is formed within the wall of the fifth flow channel 63, communicating with the exhaust side of the second blade group 52. The sixth flow channel 631 communicates with the outside of the second guide 6, thereby providing a thermal shielding effect for the high-temperature airflow within the third flow channel 61 and preventing the airflow temperature within the fifth flow channel 63 from becoming too high. To facilitate airflow within the sixth flow channel 631, a drainage hole 632 is provided on the wall of the fifth flow channel 63.
[0055] In some embodiments, the first guide vane 3, the turbine rotor 5, and the second guide vane 6 are all integral structures, formed by 3D printing, to simplify the component structure, reduce the number of components and the overall weight while meeting functional requirements, thereby improving the power-to-weight ratio of the equipment. The first guide vane 3 includes a flow-guiding body structure, which can be regarded as a turbine stator casing, and also includes stator blades 4, which are located at the outlet of the first flow channel 31 of the first guide vane 3. The integral forming of the second guide vane 6 should be understood as the overall structure of the second guide vane 6, including the cooling pipes passing through the second guide vane 6, i.e., the pipes of the fifth flow channel 63, and the fuel pipe 10, being an integral structure with the second guide vane 6. It can be regarded as part of the second guide vane 6, and the second guide vane integrates the functions of the fifth flow channel 63 and the fuel pipe 10.
[0056] like Figure 5As shown, in this invention, the high-temperature gas discharged from the gas generator passes through the first flow channel 31, performs work on the first blade assembly 51, and is then discharged from the third flow channel 61. This fluid route is the high-temperature gas flow path 001. In this invention, gas from outside the turbine generator is introduced into the cavity 33 inside the first guide vane through the second flow channel 32. Driven by the second blade assembly 52, the second blade assembly 52 performs work on the gas, pressurizing and transporting the gas in the cavity 33 to the fourth flow channel 62, and further to the second... The fluid passage formed between the sleeve 9 and the first sleeve 8 is then discharged, and this passage is the first cooling passage 002; in this invention, the fifth passage 63 introduces air from outside the turbine generator, passes through the inside of the generator 7, and is discharged through the exhaust impeller 11, which is the second cooling passage 003; in this invention, oil enters from one side through the fuel pipe 10, passes through the fluid passage between the first sleeve 8 and the generator 7 housing, and is transported around the motor housing to the oil discharge end of another fuel pipe 10, which is the third cooling passage 004.
[0057] On the other hand, this utility model also provides an aviation power device, including the turbine generator described above, which supplies power to the connected aircraft motor and / or battery, thereby enabling the turbine generator, aircraft motor, and battery to form a highly efficient and reliable power propulsion device.
[0058] The above description is merely a preferred embodiment of this application and is not intended to limit this application in any way. Although this application has disclosed the preferred embodiment as above, it is not intended to limit this application. Any person skilled in the art can make some modifications or alterations to the above-mentioned technical content to create equivalent embodiments without departing from the scope of the technical solution of this utility model. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of this application without departing from the content of the technical solution of this application shall still fall within the scope of this application.
Claims
1. A turbine power generation device, characterized in that, include: The first flow guide (3) has a first flow channel (31) arranged along its axial direction and a cavity (33) formed therein, the cavity (33) being connected to the outside of the first flow guide (3) through a second flow channel (32); The turbine rotor (5) has a first blade group (51) and a second blade group (52), wherein the first blade group (51) is mounted on the outer periphery of the second blade group (52); The second guide vane (6) is installed between the first guide vane (3) and the second guide vane (6); The first flow channel (31) is connected to the first blade group (51), and the second flow channel (32) is connected to the second blade group (52). The first blade group (51) is designed to drive the turbine rotor (5) to rotate, and the second blade group (52) is designed to extract the gas in the cavity (33). The turbine rotor (5) drives the generator (7) to generate electricity, and the generator (7) has a heat dissipation flow channel (71) inside.
2. The turbine power generation device as described in claim 1, characterized in that, The second flow guide (6) has a third flow channel (61) and a fourth flow channel (62) that are respectively connected to the flow channels of the first blade group (51) and the second blade group (52).
3. The turbine power generation device as described in claim 1, characterized in that, The second flow guide (6) is provided with a plurality of fifth flow channels (63) that connect to the outside of it, and the fifth flow channels (63) are connected to the heat dissipation flow channel (71).
4. The turbine power generation device as described in claim 1, 2, or 3, characterized in that, The generator (7) is fitted with a first sleeve (8), and a fluid channel is formed between the first sleeve (8) and the outer casing of the generator.
5. The turbine power generation device as described in claim 1, characterized in that, The inlet end of the first flow guide (3) is connected to the exhaust end of the gas generator (1).
6. The turbine power generation device as claimed in claim 1, characterized in that, The cavity (33) is connected to the outside of the first flow channel (31) through several tubular structures.
7. The turbine power generation device as described in claim 2, characterized in that, The first flow guide (3), the turbine rotor (5), the second flow guide (6) and the generator (7) are connected in sequence, and the third flow channel (61) is designed to be arranged along the axial direction.
8. The turbine power generation device as claimed in claim 3, characterized in that, The generator is connected to the outside of the second guide vane (6) at one end near the second guide vane (6) via the fifth flow channel (63).
9. The turbine power generation device as described in claim 1, 2, or 3, characterized in that, The generator is coaxially mounted with the turbine rotor (5).
10. The turbine power generation device as claimed in claim 3, characterized in that, An air extraction impeller (11) is mounted on the shaft of the generator (7).
11. The turbine power generation device as claimed in claim 4, characterized in that, A second sleeve (9) is also sleeved outside the first sleeve (8), and a fluid channel is formed between the second sleeve (9) and the first sleeve (8) that communicates with the flow channel where the second blade group (52) is located.
12. The turbine power generation device as claimed in claim 4, characterized in that, The fluid passage between the first sleeve (8) and the housing of the generator is connected to a fuel pipe (10), which passes through the fifth flow channel (63) and connects to the outside.
13. The turbine power generation device as described in claim 3 or 8, characterized in that, The fifth flow channel (63) has a sixth flow channel (631) formed inside the pipe wall, which is connected to the exhaust side of the second blade group (52). The sixth flow channel (631) is connected to the outside of the second guide (6).
14. The turbine power generation device as claimed in claim 10, characterized in that, The exhaust impeller (11) is installed at the end away from the second guide vane (6).
15. An aircraft power equipment, characterized in that, The turbine generator includes any one of claims 1-14, wherein the turbine generator supplies power to the connected aircraft motor and / or battery.