Power plant and aircraft

Abstract

The application relates to the field of aviation power technology, in particular to a power device and an aircraft. The power device comprises a turbine assembly, an exhaust pipe, a gear box and a heat insulation assembly; the exhaust pipe comprises a first end and a second end, the turbine assembly is arranged at the first end, the fuel gas discharged by the turbine assembly flows into the first end and flows out through the second end; the gear box comprises a containing portion and an extending portion, the containing portion is contained in the second end of the exhaust pipe, and the extending portion extends out of the second end; the heat insulation assembly is arranged on at least part of the surface of the containing portion. In the manner, the gear box can be extended into the exhaust pipe, the compactness of the components of the power device can be improved, the volume of the power device can be reduced, and the risk that the fuel gas damages the gear box can be reduced.

Description

Technical Field

[0001] This application relates to the field of aviation power technology, and in particular to a power unit and an aircraft. Background Technology

[0002] Power plants such as turboshaft engines typically have separate accessory gearboxes and power turbine gearboxes. As a result, the components in a turboshaft engine are relatively dispersed, which is not conducive to the compact design of the overall turboshaft engine structure. This leads to a bulky and large overall structure for the turboshaft engine, and further affects the compact design of the aircraft. Summary of the Invention

[0003] Therefore, it is necessary to provide a power unit and aircraft that can extend the gearbox into the exhaust pipe, thereby improving the compactness of the various components of the power unit, reducing the size of the power unit, and reducing the risk of damage to the gearbox by the exhaust gas, in order to address the above-mentioned technical problems.

[0004] On one hand, a power device is provided, comprising: a turbine assembly, an exhaust pipe, a gearbox, and a heat insulation component; the exhaust pipe includes a first end and a second end, the turbine assembly is disposed at the first end, and the exhaust gas emitted by the turbine assembly enters from the first end; the gearbox includes a receiving portion and an extension portion, the receiving portion is housed at the second end of the exhaust pipe, and the extension portion extends out from the second end; the heat insulation component is disposed on at least a portion of the surface of the receiving portion for blocking heat transfer between the exhaust gas and the receiving portion.

[0005] In one embodiment of this application, the exhaust pipe includes a first channel, a second channel, and an inner shell, with the inner shell disposed between the first channel and the second channel; wherein the relative direction of the first channel and the second channel is perpendicular to the axial direction of the exhaust pipe; a turbine assembly is disposed at the first end of the first channel, and a receiving portion is disposed in the second channel; a heat insulation assembly is disposed between the inner shell and the receiving portion.

[0006] In one embodiment of this application, the heat insulation component includes a connector and a heat insulation member, the connector being closer to the first end than the heat insulation member; the surface of the connector facing the first channel is connected to the inner housing; the heat insulation member is sandwiched between the inner housing and the receiving portion, and the end of the heat insulation member facing the first end is connected to the surface of the connector away from the first channel.

[0007] In one embodiment of this application, the connector includes a connecting portion and a stepped portion, the stepped portion being bent away from the first channel; the end of the heat insulation member facing the first end is clamped between the stepped portion and the receiving portion, the stepped portion and the inner shell have a deformation cavity, and the stepped portion is an elastic member.

[0008] In one embodiment of this application, the inner shell includes a main body and a bent portion; the main body is disposed on the side of the receiving portion facing the first channel; the receiving portion is provided with a limiting groove; the bent portion is embedded in the limiting groove.

[0009] In one embodiment of this application, the exhaust pipe includes an outer shell and a sealing shell. The outer shell is provided with an exhaust port. The outer shell surrounds the receiving portion, and the sealing shell is located at the second end of the exhaust pipe and between the receiving portion and the outer shell, guiding the gas to be discharged from the exhaust port.

[0010] In one embodiment of this application, the power unit further includes a compressor and a first seal; the accommodating portion includes a gas passage and a heat dissipation passage; wherein, the pressure of the gas passage is higher than the pressure of the heat dissipation passage; the gas passage is connected to the compressor, and high-pressure gas introduced from the compressor flows in the gas passage; the surface of the heat dissipation passage is attached to the surface of the heat insulation component; the gas passage and the heat dissipation passage are sealed together by the first seal; the first seal is used to prevent high-pressure gas from overflowing from the gas passage, and guides the overflowing high-pressure gas to be discharged through the heat dissipation passage when high-pressure gas overflows, so as to dissipate heat on the surface of the heat dissipation passage.

[0011] In one embodiment of this application, the heat dissipation channel includes a first chamber and an outer flow channel; the first chamber is located on the side of the first seal away from the gas channel; the outer flow channel is located on the side of the gas channel facing the heat insulation component; high-pressure gas overflowing from the gas channel enters the first chamber and is discharged through the outer flow channel.

[0012] In one embodiment of this application, the receiving portion further includes a second chamber located on the side of the gas passage away from the heat insulation component, and lubricating oil flows into the second chamber; the power device further includes a second seal, and the second chamber and the gas passage are sealed together by the second seal.

[0013] In one embodiment of this application, the gearbox includes a first transmission housing and a second transmission housing; the receiving portion includes at least a portion of the first transmission housing; the extension includes the second transmission housing; and the length of the receiving portion is greater than the length of the extension in the relative directions of the first end and the second end.

[0014] On the other hand, an aircraft is provided, comprising: a body and a power unit as described in any of the above embodiments; the power unit is disposed on the body.

[0015] The aforementioned power unit and aircraft include a gearbox comprising a housing portion housed within an exhaust pipe and an extension portion of the exhaust pipe that does not extend into it. Unlike related technologies where the gearbox is located at the very end of the power unit, this application allows a portion of the gearbox to extend into the exhaust pipe, thereby improving the compactness of the power unit and reducing its overall size. Simultaneously, heat insulation components are provided on at least a portion of the housing portion to prevent heat transfer between the exhaust gas and the housing portion, thus reducing the risk of the gearbox overheating due to high-temperature exhaust gas and consequently reducing the risk of gearbox damage from high temperatures. This, in turn, helps ensure the reliability of the gearbox and the power unit. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of an embodiment of the power device of this application;

[0017] Figure 2 yes Figure 1 A schematic diagram of the cross-sectional structure of the power unit along the AA direction.

[0018] Figure 3 yes Figure 2 A partially enlarged schematic diagram of region α of the power unit shown;

[0019] Figure 4 This is a schematic diagram of the structure of an embodiment of the exhaust pipe of this application;

[0020] Figure 5 This is a schematic diagram of the structure of an embodiment of the thermal insulation component of this application;

[0021] Figure 6 This is a schematic diagram of the structure of one embodiment of the connector in this application;

[0022] Figure 7 This is a schematic diagram of the structure of an embodiment of the heat insulation component of this application. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0024] To address the technical problem of a bulky power unit structure due to the low compactness of its components, this application provides a power unit and an aircraft. In this application, the relative positions of the gearbox and exhaust pipe of the power unit are changed, at least a portion of the gears of the power unit extend into the exhaust pipe, and a heat insulation component is provided on the surface of the gearbox to overcome the problem of the high temperature of the exhaust gas easily damaging the gearbox. The following is a detailed description of this application.

[0025] Please refer to the following: Figures 1 to 3, Figure 1 This is a schematic diagram of the structure of an embodiment of the power device of this application. Figure 2 yes Figure 1 The diagram shows a cross-sectional view of the power unit along the AA direction. Figure 3 yes Figure 2 This is a partially enlarged schematic diagram of region α of the power unit shown. In this embodiment, the power unit can be applied to environments such as aircraft and vehicles, and is not limited thereto.

[0026] In one embodiment, the power unit includes a turbine assembly 10, a gearbox 20, a heat insulation assembly 30, and an exhaust pipe 40.

[0027] Turbine assembly 10 is a rotary power machine that converts the energy of a flowing working fluid into mechanical work; it can be considered equivalent to a fan in a car or airplane engine. Turbine assembly 10 can improve engine performance by using exhaust gases to blow fuel vapor into the engine. Turbine assembly 10 is one of the main components of power plants such as aircraft engines, gas turbines, and steam turbines. Figure 2 As illustrated in the example, the turbine assembly 10 may include a turbine component 11 and a turbine casing 12, with the turbine component 11 disposed in the turbine casing 12.

[0028] The exhaust pipe 40 is capable of discharging high-temperature combustion gases generated by the turbine assembly 10. The exhaust pipe 40 may include a first end 41 and a second end 42. The turbine assembly 10 is disposed at the first end 41 of the exhaust pipe 40. The combustion gases discharged by the turbine assembly 10 enter through the first end 41.

[0029] The gearbox 20 is a widely used mechanical component in wind turbine generator sets. The gearbox 20 transmits the power generated by the wind turbine under wind force to the generator, enabling it to achieve the corresponding rotational speed. In this embodiment, the gearbox 20 includes a housing portion 21 and an extension portion. The housing portion 21 of the gearbox 20 is housed at the second end 42 of the exhaust pipe 40, and the extension portion extends out from the second end 42.

[0030] In other words, in this embodiment, the gearbox 20 extends into the exhaust pipe 40. Compared with the related art where the gearbox 20 is completely located at the far end of the exhaust pipe 40, this embodiment changes the traditional layout of the components in the power unit by changing the setting position of the gearbox 20, effectively improving the compactness of the power unit mechanism and reducing the overall size of the power unit, which is beneficial to the compact design of the power unit and the aircraft.

[0031] A heat insulation component 30 is disposed on at least a portion of the surface of the receiving portion 21. As the name suggests, the heat insulation component 30 can block heat transfer. In one embodiment, the heat insulation component 30 can block heat transfer between the combustion gas and the receiving portion 21, thereby preventing heat from being transferred from the combustion gas to the gearbox 20, thus reducing the risk of the gearbox 20 being affected or even damaged by high temperatures, and thus helping to ensure the safety and reliability of the power unit.

[0032] For example, the heat insulation component 30 may be provided on the surface of the receiving portion 21 near the turbine assembly 10; or, the heat insulation component 30 may be provided on the surface of the receiving portion 21 near the gas flow passage; or, the heat insulation component 30 may be provided on all surfaces of the receiving portion 21; or, the heat insulation component 30 may be provided on all surfaces of the receiving portion 21, while the heat insulation component 30 may also be provided on at least a portion of the extension on the surface near the receiving portion 21, without limitation.

[0033] Therefore, in this embodiment, a portion of the gearbox 20 can extend into the exhaust pipe 40, which helps to improve the compactness of the power unit and thus reduce its size. Simultaneously, a heat insulation component 30 is provided on at least a portion of the surface of the accommodating portion 21 to prevent heat transfer between the exhaust gas in the exhaust pipe 40 and the accommodating portion 21. This reduces the risk of the high-temperature exhaust gas causing the gearbox 20 to overheat, thereby reducing the risk of damage to the gearbox 20 due to high temperatures and ultimately ensuring the reliability of the gearbox 20 and the power unit.

[0034] Please continue reading. Figures 1 to 3 In one embodiment, the length of the receiving portion 21 is greater than the length of the extension portion along the direction opposite to the first end 41 and the second end 42 of the exhaust pipe 40. In other words, the length of the receiving portion 21 housed in the exhaust pipe 40 is greater than the length of the extension portion not housed in the exhaust pipe 40, thereby effectively improving the compactness of the power unit.

[0035] Specifically, the gearbox 20 may include a first transmission housing and a second transmission housing.

[0036] The receiving portion 21 includes at least a portion of the first transmission housing. The extension includes a second transmission housing.

[0037] like Figure 1 and Figure 2 As illustrated in the example, the first transmission housing may extend into the exhaust pipe 40 as a receiving portion 21. The length of the first transmission housing may account for approximately 70% of the overall length of the gearbox 20. Referring to the dimensions of power units such as turboshaft engines in related technologies, when the first transmission housing is housed within the exhaust pipe 40, the overall length of the turboshaft engine can be reduced by approximately 16%.

[0038] It should be noted that, as Figure 1 as well as Figure 2 As illustrated in the example, the length of the exhaust pipe 40 may vary at different positions along its axis, as shown in the figure. The maximum length of the accommodating portion 21 at each position can be taken as the length of the accommodating portion 21. Therefore, Figure 1 as well as Figure 2 As illustrated in the example, the length of the accommodating part 21 is the same as the length of the complete first transmission housing.

[0039] In an alternative embodiment, a portion of the first transmission housing may be housed within the exhaust pipe 40 as a housing portion 21.

[0040] Furthermore, the cross-sectional area of ​​the first transmission casing perpendicular to its extension direction gradually decreases along the direction close to the first end 41 of the exhaust pipe 40, so as to reserve sufficient space inside the exhaust pipe 40 for exhaust gas discharge, which can facilitate the reliable discharge of gas, thereby reducing the risk of gas accumulating in the exhaust pipe 40 and damaging the power unit or even posing safety hazards, and thus further improving the reliability of the power unit.

[0041] Optionally, the surface of the first transmission casing can be conical, which facilitates the flow of gas and effectively reduces the risk of gas accumulation. In alternative embodiments, the surface of the first transmission casing can also be convex or concave, and this is not limited thereto.

[0042] Please continue to refer to the following: Figures 2 to 3 In one embodiment, the exhaust pipe 40 includes a first channel 43, a second channel 44, and an inner housing 45.

[0043] The inner housing 45 is disposed between the first channel 43 and the second channel 44, thereby dividing the exhaust pipe 40 into at least two spaces. The relative directions of the first channel 43 and the second channel 44 are perpendicular to the axial direction of the exhaust pipe 40.

[0044] Specifically, the turbine assembly 10 is located at the first end 41 of the first channel 43, that is, the first channel 43 can discharge the high-temperature gas generated by the turbine assembly 10, that is, the gas flows in the first channel 43.

[0045] The receiving part 21 is housed in the second channel 44, thereby separating the flow space of the gas from the receiving space of the receiving part 21 through the physical structure, reducing the amount of gas flowing through the receiving part 21 of the gearbox 20, thereby reducing the contact area between the receiving part 21 and the gas, and further helping to reduce the heat transfer of the gas to the gearbox 20.

[0046] The heat insulation component 30 is disposed between the inner shell 45 and the receiving portion 21. In this way, the inner shell 45 can preferentially block the heat of the combustion gas, and the heat insulation component 30 further blocks the heat transfer to the gearbox 20. At the same time, this embodiment can further effectively reduce the risk of combustion gas corroding the heat insulation component 30, which is beneficial for extending the service life of the heat insulation component 30, thereby further improving the reliability of the power unit and saving costs.

[0047] Optionally, a gap exists between the turbine assembly 10 and the inner housing 45 to ensure the safety and reliability of the inner housing 45, reduce the risk of the turbine assembly 10, a rotating component, damaging the relatively stationary inner housing 45, and further improve the reliability of the power unit in this embodiment.

[0048] In an alternative embodiment, the thermal insulation component 30 may also be disposed on the surface of the inner housing 45 opposite to the receiving portion 21, thereby facilitating the replacement of the thermal insulation component 30.

[0049] Furthermore, the inner housing 45 may include a main body 451 and a bent portion 452. The main body 451 is provided on the side of the receiving portion 21 facing the first channel 43. The receiving portion 21 of the gearbox 20 may be provided with a limiting groove 211. The bent portion 452 is embedded in the limiting groove 211. In this way, the stability of the inner housing 45 assembly can be improved by the limiting groove 211, which helps to reduce the risk of deformation or damage to the end of the inner housing 45 near the turbine assembly 10.

[0050] Please refer to the following: Figures 2 to 4 , Figure 4 This is a schematic diagram of an embodiment of the exhaust pipe of this application.

[0051] In one embodiment, the exhaust pipe 40 may further include an outer casing 46 and a sealing casing 47.

[0052] The outer casing 46 surrounds the receiving portion 21. The outer casing 46 is provided with an exhaust port 461, which is used to discharge the gas flowing through the exhaust pipe 40.

[0053] The sealing housing 47 is located at the second end 42 of the exhaust pipe 40 and is located between the accommodating portion 21 and the outer casing 46 to prevent the gas from flowing out from the second end 42 and guide the gas to be discharged from the exhaust port 461. This rationally arranges the gas flow direction and can further reduce the damage of the gas to the extension portion 22 of the gearbox 20 compared to the gas and the second end 42.

[0054] The specific structure of the thermal insulation component 30 of this application is illustrated below with examples.

[0055] Please refer to the following: Figure 3 , Figures 5 to 7 , Figure 5This is a schematic diagram of the structure of an embodiment of the thermal insulation component of this application; Figure 6 This is a schematic diagram of the structure of one embodiment of the connector in this application; Figure 7 This is a schematic diagram of the structure of an embodiment of the heat insulation component of this application.

[0056] In one embodiment, the thermal insulation assembly 30 may include a connector 31 and a thermal insulation component 32, with the connector 31 being closer to the first end 41 than the thermal insulation component 32. As the name suggests, the thermal insulation component 32 is the component that specifically performs the thermal insulation function, and the connector 31 serves to connect and fix the thermal insulation component 32.

[0057] Specifically, the connecting member 31 connects to the inner housing 45 on the surface facing the first channel 43. The heat insulation member 32 is sandwiched between the inner housing 45 and the receiving portion 21, and the end of the heat insulation member 32 facing the first end 41 connects to the surface of the connecting member 31 away from the first channel 43. In this way, when replacing the heat insulation member 32, the heat insulation member 32 can be directly removed from the connecting member 31, thereby reducing damage to the inner housing 45 as a whole.

[0058] It is easy to understand that the heat insulation component 32 can also be directly disposed between the inner housing 45 and the receiving part 21. By fixing the heat sink between the inner housing 45 and the receiving part 21 through welding, adhesive, or other methods, replacing the heat insulation component 32 may cause some damage to the inner housing 45 and the receiving part 21, but it can still effectively prevent heat transfer between the gas and the gearbox 20. In this embodiment, to further reduce the risk of damage to the power unit, a connector 31 is used to connect to a small portion of the surface of the inner housing 45 to reduce damage to the power unit when replacing the heat sink / heat dissipation assembly.

[0059] Optionally, the connector 31 and the heat insulation component 32, as well as the connector 31 and the outer shell surfaces of the inner shell 45 and the exhaust pipe 40, can be connected by welding, adhesive, or other means.

[0060] Furthermore, the connector 31 may include a connecting portion 311 and a stepped portion 312. The stepped portion 312 is bent away from the first channel 43. The end of the heat insulation member 32 facing the first end 41 may be clamped between the stepped portion 312 and the receiving portion 21.

[0061] Thus, a deformation cavity 50 is provided between the stepped portion 312 and the inner housing 45, and the stepped portion 312 can elastically deform toward the deformation cavity 50. This further facilitates the replacement of the heat sink. The stepped portion 312 can be an elastic element capable of elastic deformation.

[0062] Furthermore, the heat insulation element 32 can be disposed on the entire surface of the first transmission housing. Optionally, as illustrated in the foregoing embodiments, the cross-sectional area of ​​the first transmission housing perpendicular to its extending direction gradually decreases along the direction near the first end 41 of the exhaust pipe 40. The cross-sectional area of ​​the heat insulation element 32 perpendicular to its extending direction can also gradually decrease along the direction near the first end 41 of the exhaust pipe 40 to improve the heat insulation effect of the heat insulation element 32. Optionally, the heat insulation element 32 can be heat insulation cotton, heat insulation sheet, etc., and is not limited thereto.

[0063] Please continue reading. Figure 2 as well as Figure 3 In one embodiment, the power unit further includes a compressor (not shown) and a first seal 61.

[0064] The receiving portion 21 includes a gas passage 212 and a heat dissipation passage 213. The pressure in the gas passage 212 is higher than the pressure in the heat dissipation passage 213. The surface of the heat dissipation passage 213 can be attached to the surface of the heat insulation component 30.

[0065] A turboshaft engine is a component that uses high-speed rotating blades to perform work on air and increase its pressure. The curved tip of the compressor impeller blades is called a guide wheel, which guides the gas into the working impeller without impact, reducing airflow impact losses.

[0066] Specifically, gas passage 212 can be connected to a compressor. High-pressure gas introduced from the compressor flows through gas passage 212. Optionally, gas passage 212 can be connected to an intermediate stage of the compressor, so that a portion of high-pressure gas drawn from the intermediate stage of the compressor is introduced into gas passage 212.

[0067] Optionally, such as Figure 3 As illustrated in the example, gas passage 212 may include a connected storage chamber and an inner flow channel. The storage chamber is used to store high-pressure gas, and the inner flow channel is used to connect to a compressor. High-pressure gas is introduced from the inner flow channel and flows to the storage chamber.

[0068] Meanwhile, please continue to refer to Figure 2 as well as Figure 3 In one embodiment, the heat dissipation channel 213 is connected to the outside of the power unit, that is, the heat dissipation channel 213 is connected to the air. Since the gas channel 212 stores high-pressure gas, the pressure in the gas channel 212 is higher than the pressure in the heat dissipation channel 213.

[0069] Furthermore, the gas passage 212 and the heat dissipation passage 213 are sealed together by the first sealing element 61.

[0070] The first seal 61 can prevent high-pressure gas from overflowing from the gas passage 212. However, considering that although the sealing device can reduce the overflow of high-pressure gas, a small amount of high-pressure gas leakage is unavoidable. In this embodiment, the overflowing high-pressure gas can be fully utilized through the heat dissipation passage 213 and the first seal 61.

[0071] In this embodiment, when high-pressure gas overflows, it can be guided to exit through the heat dissipation channel 213. The pressure in the heat dissipation channel 213 is lower than the pressure in the gas channel. Due to the pressure difference and the structure of the heat dissipation channel 213, the high-pressure gas can flow towards and exit through the heat dissipation channel 213. Because there is gas flow within the heat dissipation channel 213, airflow passes over its surface, carrying the heat absorbed by the heat dissipation components and thus dissipating heat from the surface of the heat dissipation channel 213.

[0072] In other words, this embodiment further considers that the heat insulation component 30 can block heat transfer to the gearbox 20, but the heat insulation component 30 itself may heat up. If so, a temperature difference may still exist between the heat insulation component 30 and the gearbox 20, and the gearbox 20 may absorb the heat transferred by the heat insulation component 30. Similarly, since heat transfer is blocked by the heat insulation component 30 in this embodiment, the gearbox 20 will not experience a significant and rapid temperature increase even if it heats up.

[0073] Therefore, in this embodiment, a heat dissipation channel 213 is additionally provided near the gearbox 20, which can reduce the impact of temperature rise on other components of the gearbox 20. Furthermore, the airflow formed by the overflowing high-pressure gas can be used to dissipate heat from the walls of the heat dissipation channel 213, achieving a sufficient heat dissipation effect.

[0074] For example, the first seal 61 can be as follows: Figure 3 The example shown is a sieve. In an alternative embodiment, the first seal 61 may also be a sealing ring, etc., and is not limited thereto.

[0075] Please continue reading. Figure 2 as well as Figure 3 In one embodiment, the heat dissipation channel 213 may include a communicating first chamber 2131 and an external flow channel 2132.

[0076] The first chamber 2131 is located on the side of the first seal 61 away from the gas passage 212, and the first chamber 2131 can buffer the pressure of the overflowing high-pressure gas. The outer flow channel 2132 is located on the side of the gas passage 212 facing the heat insulation component 30, and the outer flow channel 2132 can connect to the external environment.

[0077] High-pressure gas overflowing from the gas passage 212 via the first seal 61 can enter the first chamber 2131 and then be discharged through the outer flow passage 2132. The first chamber 2131 serves as a transition, preventing high-pressure gas from flowing into the first passage 43 of the exhaust pipe 40, and also preventing the combustion gas generated by the turbine assembly 10 from entering the gearbox 20, thereby reducing the risk of the gearbox 20 being affected by high temperatures, which helps to improve the reliability of the power unit and extend its service life.

[0078] Optionally, as described above, the receiving portion 21 includes a limiting groove 211 that can be embedded in the bending portion 452 of the inner shell 45. The limiting groove 211 can be provided in the first chamber 2131 to further rationalize the structural layout of the power device in this embodiment, thereby improving the compactness of the power device.

[0079] Please continue reading. Figure 2 as well as Figure 3 In one embodiment, the receiving portion 21 may further include a second chamber 214. The second chamber 214 is located on the side of the gas passage 212 away from the heat insulation component 30, and lubricating oil flows in the second chamber 214, which helps to reduce the risk of the lubricating oil overheating and deteriorating.

[0080] The power unit may also include a second seal 62, which seals the second chamber 214 to the gas passage 212, thereby preventing lubricating oil from flowing to the gas passage 212.

[0081] For example, the second seal 62 can be as follows: Figure 3 The example shown is a sieve. In an alternative embodiment, the second seal 62 can also be a sealing ring, etc., and is not limited thereto.

[0082] Optionally, the power unit may include both a first seal 61 and a second seal 62, forming three pressure zones inside the power unit, thereby rationally planning the internal layout of the power unit and placing the same pressure zone. The first pressure zone is a gas passage 212, which is a high-pressure zone; the second pressure zone is a heat dissipation passage 213; and the third pressure zone is a second chamber 214.

[0083] In summary, the power unit of this application integrates the gearbox 20 into the exhaust pipe 40, and provides a heat insulation component 30 on the surface of the exhaust pipe 40 to reduce the risk of the high temperature of the combustion gas affecting or even damaging the gearbox 20. Simultaneously, the rationally designed channels in this application introduce high-pressure gas from the compressor to further dissipate heat from the gearbox 20. Furthermore, the reasonable airflow layout design enables timely heat dissipation, which helps ensure the performance and safety of the gearbox 20.

[0084] Meanwhile, this application features numerous refined design details, such as the inner shell's bent portion being housed in a limiting groove to ensure reliable assembly, the connecting parts having bent steps to facilitate deformation, a rational layout of the pressure zones inside the gearbox, and the use of overflowing high-pressure gas for further heat dissipation while the heat insulation components block heat. These details, as disclosed in detail above, will not be repeated here. This application can significantly improve the operational stability and safety of the power unit, thereby helping to improve the compactness of the power unit's structure while ensuring its performance and safety.

[0085] In one embodiment, the power unit can be applied to an aircraft.

[0086] In this embodiment, the aircraft may include a main body and a power unit as described in any of the preceding embodiments.

[0087] The main body is a collection of basic components and parts that enable flight functions. For example, the main body may include the aircraft's controller, wings, landing gear, fuel tank and / or battery, etc., which will not be elaborated further here.

[0088] The power unit can be located on the aircraft. In this embodiment, by improving the structural compactness of the power unit and reducing its size, it is even more beneficial to reduce the volume of the aircraft.

[0089] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0090] The above embodiments merely illustrate several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A power unit, characterized in that, The power unit includes: Turbine assembly; An exhaust pipe includes a first end and a second end, the turbine assembly is disposed at the first end, and the exhaust gas emitted by the turbine assembly enters from the first end; A gearbox includes a receiving portion and an extension portion, the receiving portion being received at a second end of the exhaust pipe, and the extension portion extending out from the second end; A heat insulation component is disposed on at least a portion of the surface of the receiving portion to prevent heat transfer between the gas and the receiving portion; The exhaust pipe includes a first channel, a second channel, and an inner shell, with the inner shell disposed between the first channel and the second channel; The turbine assembly is located at the first end of the first channel, and the receiving portion is located in the second channel; the heat insulation assembly is located between the inner shell and the receiving portion; Compressor and first seal; The accommodating portion includes a gas passage and a heat dissipation passage; wherein the pressure in the gas passage is higher than the pressure in the heat dissipation passage; The gas channel is connected to the compressor, and high-pressure gas introduced from the compressor flows through the gas channel; the surface of the heat dissipation channel is attached to the surface of the heat insulation component. The gas channel and the heat dissipation channel are sealed together by the first sealing element; the first sealing element is used to prevent high-pressure gas from overflowing from the gas channel, and to guide the overflowing high-pressure gas to be discharged through the heat dissipation channel when it overflows, so as to dissipate heat on the surface of the heat dissipation channel.

2. The power unit according to claim 1, characterized in that, The heat insulation component includes a connector and a heat insulation component, wherein the connector is closer to the first end relative to the heat insulation component; The connector is connected to the inner housing on the surface facing the first channel; The heat insulation element is sandwiched between the inner housing and the receiving portion, and the end of the heat insulation element facing the first end is connected to the surface of the connector away from the first channel.

3. The power unit according to claim 2, characterized in that, The connector includes a connecting portion and a stepped portion, wherein the stepped portion is bent toward a direction away from the first channel; The end of the heat insulation member facing the first end is clamped between the stepped portion and the receiving portion, and there is a deformation cavity between the stepped portion and the inner shell. The stepped portion is an elastic member.

4. The power unit according to claim 1, characterized in that, The inner housing includes a main body and a bent portion; the main body is located on the side of the receiving portion facing the first channel; The receiving portion is provided with a limiting groove; the bent portion is embedded in the limiting groove.

5. The power unit according to claim 1, characterized in that, The exhaust pipe includes an outer shell and a sealing shell. The outer shell is provided with an exhaust port. The outer shell surrounds the receiving portion, and the sealing shell is located at the second end of the exhaust pipe and between the receiving portion and the outer shell, guiding the gas to be discharged from the exhaust port.

6. The power unit according to claim 1, characterized in that, The heat dissipation channel includes a first chamber and an outer flow channel; the first chamber is located on the side of the first seal away from the gas channel; the outer flow channel is located on the side of the gas channel facing the heat insulation component; high-pressure gas overflowing from the gas channel enters the first chamber and is discharged through the outer flow channel.

7. The power unit according to claim 6, characterized in that, The accommodating portion further includes a second chamber located on the side of the gas passage away from the heat insulation component, and lubricating oil flows into the second chamber; The power unit also includes a second seal, and the second chamber and the gas passage are sealed together by the second seal.

8. The power unit according to claim 1, characterized in that, The gearbox includes a first transmission housing and a second transmission housing; The receiving portion includes at least a portion of a first transmission housing; the extension includes a second transmission housing; the length of the receiving portion is greater than the length of the extension in the direction relative to the first end and the second end.

9. An aircraft, characterized in that, The aircraft includes: ontology; The power unit as described in any one of claims 1 to 8 is disposed on the main body.

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