Heat dissipation device of cruise power module, cruise power module and aircraft

Abstract

The utility model provides a cruise power module heat dissipation device, a cruise power module and an aircraft, and belongs to the technical field of aircrafts. Through the structural design of a propeller fairing, a heat exchanger and an inner hot air exhaust pipeline and the aerodynamic layout characteristics of an electric vertical take-off and landing aircraft, the heat exchanger is arranged in a power arm body at the inner end of a cruise motor; according to the power arm, the air entraining fan blades are arranged on the inner wall of the propeller fairing, when the propeller rotates, the propeller fairing is synchronously driven to rotate, so that the air entraining fan blades are driven to rotate, and external cold air can be sucked into the power arm body under the condition of no air speed; in combination with incoming flow in a cruise flight state, cold air flows through a cruise motor and a heat exchanger, hot air subjected to heat exchange is exhausted out of a power arm body through an inner hot air exhaust pipeline, and the heat exchange efficiency is greatly improved; the curved propeller fairing can reduce cruise resistance; the utility model has the advantages of high heat exchange efficiency, light structural weight, reduced cruise resistance and the like.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, more specifically, a cruising power module heat dissipation device, cruising power module and aircraft. BACKGROUND

[0002] EVTOL (electric vertical take-off and landing aircraft) is a new type of aircraft, which is derived from the demand for efficient, convenient and green and clean urban air traffic. The traditional helicopter has problems such as high noise, high cost and complex operation. EVTOL combines electric technology to reduce noise and operation and maintenance costs. Because it has the ability of vertical take-off and landing, it does not need a special runway and can take off and land in a small space. It combines technologies from multiple fields such as aviation, electricity and intelligent control, providing a new solution for urban air travel, logistics, emergency rescue and other scenarios, and has a wide range of application scenarios.

[0003] Since the power of large EVTOL is a high-power motor, it is not suitable for natural cooling, so the existing main cooling schemes are air cooling and liquid cooling. Air cooling usually designs cooling fins on the motor, and uses a propeller or an additional cooling fan to remove heat; the liquid cooling method is more direct and effective, and the cooling liquid can directly contact the area with the most serious heat, and the heat is taken to the heat exchanger through the cooling pipeline for heat exchange to dissipate heat.

[0004] The current cruising power module generally uses a cooling method that exposes cooling fins or cooling fans outside the power arm, uses air flow through the fins or air flow introduced by the cooling fan to achieve heat exchange. This cooling method causes some flight resistance when the aircraft is cruising, and the heat exchange efficiency is low. UTILITY MODEL CONTENTS

[0005] In view of the above problems, the utility model aims to provide a cruising power module heat dissipation device, cruising power module and aircraft to solve the problem that in the prior art, cooling fins or cooling fans need to be exposed outside the power arm to use air flow through the fins or air flow introduced by the cooling fan to achieve heat exchange, which causes some flight resistance when the aircraft is cruising, and the heat exchange efficiency is low.

[0006] The utility model provides a cruising power module heat dissipation device, which comprises a propeller fairing, a heat exchanger and an inner hot gas exhaust pipeline, wherein,

[0007] The propeller fairing is a von Karman curve fairing with a narrow front and a wide back, the propeller fairing is installed on the propeller, and the blades of the propeller are located outside the propeller fairing; the cruise motor of the propeller is arranged inside the power arm body; the rear end of the propeller fairing is fixed at the hub end of the propeller; air guide vanes are arranged on the inner wall of the front end of the propeller fairing.

[0008] The heat exchanger is arranged inside the power arm body, and comprises a first heat exchanger and a second heat exchanger arranged on both sides of the inner end of the cruise motor respectively; the first heat exchanger and the second heat exchanger are connected in series through a first cooling liquid pipe; the hot liquid inlet and the cold liquid outlet of the heat exchanger are connected with the cooling liquid outlet pipe and the cooling liquid inlet pipe of the cruise motor through a second cooling liquid pipe respectively; a hot gas channel is formed between the first heat exchanger, the second heat exchanger and the inner side wall of the power arm body.

[0009] The second cooling liquid pipe and the cooling liquid outlet pipe of the cruise motor are connected through a clamp sleeve pipe joint, and the second cooling liquid pipe and the cooling liquid inlet pipe of the cruise motor are connected through a clamp sleeve pipe joint.

[0010] The air inlet end of the inner hot gas exhaust pipe is connected with the hot gas channel, and the air outlet end of the inner hot gas exhaust pipe is connected with the hot gas exhaust port arranged on the side wall of the power arm body.

[0011] In addition, preferably, a propeller outlet is arranged on the propeller fairing; the blades of the propeller pass through the propeller outlet and are located outside the propeller fairing.

[0012] In addition, preferably, the inner hot gas exhaust pipe is fixed inside the power arm body through an exhaust pipe mounting support.

[0013] In addition, preferably, the exhaust pipe mounting support is detachably fixed inside the power arm body.

[0014] In addition, preferably, the cruise motor is fixed inside the power arm body through a cruise motor mounting support.

[0015] In addition, preferably, the cruise motor mounting support is detachably fixed inside the power arm body.

[0016] In addition, preferably, an upper maintenance opening is arranged on the upper part of the power arm body; an upper maintenance opening cover is arranged at the upper maintenance opening; and / or a lower maintenance opening is arranged on the lower part of the power arm body; a lower maintenance opening cover is arranged at the lower maintenance opening.

[0017] Further, preferably, the hot air exhaust port is disposed behind the front enlarged area of the power arm body.

[0018] The utility model also provides a kind of aircraft cruising power module, including cruising power module body, cruising power module heat dissipation device as described above is provided on the cruising power module body.

[0019] The utility model also provides a kind of electric vertical take-off and landing aircraft, including aircraft body, cruising power module is set on the aircraft body, cruising power module heat dissipation device as described above is provided on the cruising power module.

[0020] From the above technical solution, the cruising power module heat dissipation device, the cruising power module and the aircraft provided by the utility model are characterized in that: the heat exchanger is arranged in the power arm body behind (inner end) the cruising motor by the structural design of the propeller fairing, the heat exchanger and the inner hot air exhaust pipeline, combined with the characteristics of the aerodynamic layout of the electric vertical take-off and landing aircraft, the air guide fan blades are arranged on the inner wall of the narrow end of the propeller fairing, and the air guide fan blades are driven to rotate simultaneously when the propeller rotates, so that the external cold air can be sucked into the power arm body without air speed. BRIEF DESCRIPTION OF DRAWINGS

[0021] Other purposes and results of the utility model will be more apparent and easy to understand by referring to the following description in conjunction with the drawings and with a more comprehensive understanding of the utility model.

[0022] Figure 1 It is an external structure schematic view of the cruising power module heat dissipation device according to the embodiment of the utility model;

[0023] Figure 2 It is an internal structure schematic view of the cruising power module heat dissipation device according to the embodiment of the utility model;

[0024] Figure 3 It is a principle structure schematic view of the cruising power module heat dissipation device according to the embodiment of the utility model;

[0025] Figure 4 It is a heat dissipation flow chart of the aircraft cruising power module using the embodiment of the utility model.

[0026] In the drawings, 1-propeller fairing, 11-bleed fan blade, 12-propeller exit, 2-heat exchanger, 21-first heat exchanger, 22-second heat exchanger, 3-internal hot gas exhaust duct, 31-exhaust duct mounting support, 4-propeller, 5-cruise motor, 51-cruise motor mounting bracket, 6-power arm body, 61-hot gas exhaust port, 62-upper maintenance port cover, 63-lower maintenance port cover, 71-first cooling liquid guide pipe, 72-second cooling liquid guide pipe.

[0027] The same reference numbers in all the drawings indicate corresponding or analogous features or functions. DETAILED DESCRIPTION

[0028] In the following description, for the purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of one or more embodiments. It is apparent, however, that the embodiments can be practiced without these specific details.

[0029] For the foregoing, in the prior art, the heat dissipation fins or heat dissipation fans need to be exposed outside the power arm to utilize the airflow through the fins or the airflow introduced by the heat dissipation fans to achieve heat exchange, which causes certain flight resistance when the aircraft is cruising and has low heat exchange efficiency, and a cruise power module heat dissipation device, a cruise power module and an aircraft are provided.

[0030] The specific embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0031] In order to illustrate the cruise power module heat dissipation device, the cruise power module and the aircraft provided by the present application, Figure 1 The external structure of the cruise power module heat dissipation device according to the embodiments of the present application is shown; Figure 2 The internal structure of the cruise power module heat dissipation device according to the embodiments of the present application is shown; Figure 3 The principle structure of the cruise power module heat dissipation device according to the embodiments of the present application is shown; Figure 4 The heat dissipation process of the cruise power module of the aircraft according to the embodiments of the present application is shown.

[0032] As Figures 1 to 3 The cruise power module heat dissipation device provided by the present application, comprising a propeller fairing 1, a heat exchanger 2 and an internal hot gas exhaust duct 3, wherein,

[0033] The propeller fairing 1 is a von Karman curve fairing that is narrow in front and wide in the back. The propeller fairing 1 is mounted on the propeller 4, and the blades of the propeller 4 are located outside the propeller fairing 1. The cruise motor 5 of the propeller 4 is arranged inside the power arm body 6. The rear end of the propeller fairing 1 is fixed to the hub end of the propeller 4. The front inner wall of the propeller fairing 1 is provided with bleed fan blades 11.

[0034] The heat exchanger 2 is disposed inside the power arm body 6 and includes a first heat exchanger 21 and a second heat exchanger 22, respectively located on both sides of the inner end of the cruise motor 5. The first heat exchanger 21 and the second heat exchanger 22 are connected in series via a first coolant conduit 71. The hot liquid inlet and the cold liquid outlet of the heat exchanger 2 are respectively connected to the coolant outlet pipe and the coolant inlet pipe of the cruise motor 5 via a second coolant conduit 72. A hot gas channel is formed between the first heat exchanger 21, the second heat exchanger 22, and the inner side wall of the power arm body 6.

[0035] The second coolant conduit 72 and the coolant outlet pipe of the cruise motor 5 and the coolant inlet pipe of the cruise motor 5 are both connected by a sleeve-type pipe joint;

[0036] The air inlet end of the internal hot air exhaust pipe 3 is connected to the hot air channel, and the air outlet end of the internal hot air exhaust pipe 3 is connected to the hot air exhaust port 61 provided on the side wall of the power arm body 6.

[0037] Among them, the power arm in the present invention refers to a component that connects the power unit (such as a motor and a propeller, etc.) with the main structure of the aircraft.

[0038] It should be noted that the use of coolant for liquid cooling in the cruise motor 5 is prior art. Specifically, the heat dissipation structure of the coolant in the cruise motor 5 in the present invention is prior art. Coolant enters the cruise motor 5 through the coolant inlet pipe, cools the heat-generating area, and then flows out of the coolant outlet pipe after heating. Coolant delivery is achieved by a mechanical gear pump driven by the rotation of the motor. Since this is prior art, the specific structure of this part will not be described in detail in the present invention.

[0039] The coolant is pumped to the heat exchanger 2 by a mechanical gear pump driven by the rotation of the cruise motor 5, cleverly linking the coolant flow rate with the motor speed. The faster the motor speed, the higher the power and the faster the coolant is pumped. Conversely, when the motor speed is slow or even stopped, the coolant pumping speed can also be reduced.

[0040] The first heat exchanger 21 and the second heat exchanger 22 are used in series to achieve a better heat exchange effect.

[0041] Through the structural design of the propeller fairing 1, the heat exchanger 2 and the inner hot air exhaust pipeline 3, combined with the characteristics of the aerodynamic layout of the electric vertical take-off and landing aircraft, the heat exchanger 2 is arranged in the power arm body 6 behind (inner end) the cruise motor 5, the air guide blades 11 are arranged on the inner wall of the narrow end of the propeller fairing 1, when the propeller 4 rotates, the propeller fairing 1 is synchronously driven to rotate, thereby driving the air guide blades 11 to rotate, so that the external cold air can be sucked into the power arm body 6 without air speed; combined with the incoming flow in the cruise flight state, the cold air flows through the cruise motor 5 and the heat exchanger 2, and the hot air after heat exchange is discharged from the power arm body 6 through the inner hot air exhaust pipeline 3, so that the heat exchange efficiency is greatly improved; the curved propeller fairing 1 can reduce the cruise resistance; the utility model has the advantages of high heat exchange efficiency, light structure weight and the ability to reduce cruise resistance.

[0042] As a preferred scheme of the utility model, the propeller fairing 1 is provided with a propeller outlet 12; the blade of the propeller 4 passes through the propeller outlet 12 and is located outside the propeller fairing 1.

[0043] Specifically, the propeller outlet 12 is arranged on the propeller fairing 1, so that the blade of the propeller 4 can extend outside the propeller fairing 1, thereby enabling the propeller 4 to work normally without being affected by the propeller fairing 1.

[0044] As a preferred scheme of the utility model, the inner hot air exhaust pipeline 3 is fixed in the power arm body 6 through an exhaust pipeline mounting support 31.

[0045] Specifically, the exhaust pipeline mounting support 31 can be fixed in the power arm body 6 through but not limited to welding, bolt fixing and the like, and the utility model does not make special limitation on this.

[0046] As a preferred scheme of the utility model, the exhaust pipeline mounting support 31 can be detachably fixed in the power arm body 6.

[0047] Specifically, the exhaust pipeline mounting support 31 is preferably but not limited to fixed in the power arm body 6 through a bolt, so as to facilitate dismounting and part replacement.

[0048] As a preferred scheme of the utility model, the cruise motor 5 is fixed in the power arm body 6 through a cruise motor mounting support 51.

[0049] Specifically, the cruise motor mounting support 51 can be fixed in the power arm body 6 through but not limited to welding, bolt fixing and the like, and the utility model does not make special limitation on this.

[0050] As a preferred scheme of the utility model, the cruise motor mounting support 51 can be detachably fixed in the power arm body.

[0051] Specifically, the cruise motor mounting bracket 51 is preferably but not limited to fixed in the power arm body 6 by bolts, facilitating disassembly and replacement of parts.

[0052] As a preferred scheme of the utility model, an upper maintenance opening is arranged at the upper part of the power arm body 6; an upper maintenance opening cover 62 is arranged at the upper maintenance opening; and / or a lower maintenance opening is arranged at the lower part of the power arm body 6; a lower maintenance opening cover 63 is arranged at the lower maintenance opening.

[0053] Specifically, the upper maintenance opening and the lower maintenance opening are preferably arranged corresponding to the parts where the internal components of the power arm body 6 are concentrated, so that maintenance and part replacement are more convenient.

[0054] As a preferred scheme of the utility model, the hot gas exhaust opening 61 is arranged behind the front enlarged area of the power arm body 6.

[0055] Specifically, the hot gas exhaust opening 61 is located behind the front enlarged area of the power arm body, which is a negative pressure area during cruising, and is more conducive to the airflow entering the internal air duct of the power arm body 6 from the front air guide fan blade 11.

[0056] As shown in Figure 4 The cruise power module heat dissipation device of the utility model is used for dissipating heat of the cruise power module, and comprises the following steps:

[0057] Step S1, when the aircraft is ready to start attitude conversion or normal cruising, the aircraft sends a rotating instruction to the cruise motor 5;

[0058] Step S2, the cruise motor 5 rotates according to the rotating instruction, drives the propeller 4 and the propeller fairing 1 to rotate, and further drives the air guide fan blade 11 to rotate synchronously; when the cruise motor 5 rotates, the gear pump inside the cruise motor 5 is driven to rotate, so that the cooling liquid is pumped to cool the cruise motor 5;

[0059] Step S3, inside the cruise motor, the cooling liquid with increased temperature after cooling is introduced into the heat exchanger 2 through the second cooling liquid conduit 72, and after heat exchange in the heat exchanger 2, the cooling liquid is circulated back to the cooling liquid inlet pipe of the cruise motor 5 through the second cooling liquid conduit 72;

[0060] Step S4, when the air guide fan blade 11 rotates synchronously, the airflow is introduced into the power arm body 6, the airflow passes through the cruise motor 5 from the hot gas passage, carries away the heat generated by the fins of the first heat exchanger 21 and the second heat exchanger 22, and is discharged to the outside of the power arm body 6 through the hot gas exhaust opening 61 and the internal hot gas exhaust pipe 3.

[0061] The aircraft cruising power module provided by the utility model, comprising a cruising power module body, is provided with the cruising power module heat dissipation device as described above.

[0062] The cruising power module body refers to a power structure comprising a power arm and a propeller, which is prior art and thus will not be described in detail.

[0063] The electric vertical take-off and landing aircraft provided by the utility model, comprising an aircraft body, is provided with the cruising power module heat dissipation device as described above.

[0064] The installation process of the cruising power module heat dissipation device on the aircraft body is as follows:

[0065] First, install the cruising motor mounting bracket 51 and the exhaust pipe mounting seat 31 on the power arm body 6, then install the cruising motor 5, the first heat exchanger 21 and the second heat exchanger 22, connect the second cooling liquid conduit 72, and finally install the propeller 4 and the propeller fairing 1.

[0066] When there is no air speed, cold air enters the power arm body 6 inside through the propeller fairing 1 rotating with the propeller 4, flows through the cruising motor 5 to the first heat exchanger 21 and the second heat exchanger 22, and flows out of the hot air exhaust port 61 from the inner hot gas exhaust pipe 3 after flowing through the heat exchange fins, so that cold air can flow through the heat exchange fins as long as the propeller 4 rotates even in the absence of air speed, and the cruising motor 7 is guaranteed to dissipate heat; in the normal cruising state, the incoming flow in front of the propeller fairing 1 directly enters the propeller fairing 1 to complete heat dissipation inside the power arm body 6, at this time, the rotating air guide fan blade 11 can reduce the wind pressure in front of the fairing, and further achieve the purpose of reducing the cruising resistance.

[0067] As can be seen from the above specific embodiments, the cruising power module heat dissipation device, the cruising power module and the aircraft provided by the utility model have the advantages of high heat exchange efficiency, light structure weight and reduced cruising resistance, etc.

[0068] The cruise power module heat dissipation device, the cruise power module and the aircraft according to the utility model are described above with reference to the drawings by way of example. However, those skilled in the art should understand that various improvements can be made to the cruise power module heat dissipation device, the cruise power module and the aircraft according to the utility model described above without departing from the content of the utility model. Therefore, the protection scope of the utility model should be determined by the content of the appended claims.

Claims

1. A cruise power module heat dissipation device, characterized in that: It includes propeller fairing, heat exchanger and internal hot gas exhaust duct; among which, The propeller fairing is a von Karman curve fairing that is narrow in front and wide in the rear. The propeller fairing is mounted on the propeller, and the propeller blades are located outside the propeller fairing. The cruise motor of the propeller is arranged inside the power arm body. The rear end of the propeller fairing is fixed to the hub end of the propeller. The front inner wall of the propeller fairing is provided with bleed air fan blades. The heat exchanger is arranged inside the power arm body, and includes a first heat exchanger and a second heat exchanger respectively located on both sides of the inner end of the cruise motor; the first heat exchanger and the second heat exchanger are connected in series through a first coolant conduit; the hot liquid inlet and the cold liquid outlet of the heat exchanger are respectively connected to the coolant outlet pipe and the coolant inlet pipe of the cruise motor through a second coolant conduit; a hot gas channel is formed between the first heat exchanger, the second heat exchanger and the inner side wall of the power arm body; The second coolant conduit and the coolant outlet pipe of the cruise motor and the second coolant conduit and the coolant inlet pipe of the cruise motor are both connected via a ferrule-type pipe joint; The air inlet end of the inner hot air exhaust pipe is connected to the hot air channel, and the air outlet end of the inner hot air exhaust pipe is connected to the hot air exhaust port arranged on the side wall of the power arm body.

2. The cruise power module heat dissipation device according to claim 1, characterized in that: A propeller extension port is provided on the propeller fairing; the propeller blades pass through the propeller extension port and are located outside the propeller fairing.

3. The cruise power module heat dissipation device according to claim 1, characterized in that: The internal hot gas exhaust pipe is fixed inside the power arm body through an exhaust pipe mounting bracket.

4. The cruise power module heat dissipation device according to claim 3, characterized in that: The exhaust pipe mounting bracket is detachably fixed inside the power arm body.

5. The cruise power module heat dissipation device according to claim 1, characterized in that: The cruise motor is fixed inside the power arm body through a cruise motor mounting bracket.

6. The cruise power module heat dissipation device according to claim 5, characterized in that: The cruise motor mounting bracket is detachably fixed inside the power arm body.

7. The cruise power module heat dissipation device according to claim 1, characterized in that: An upper maintenance opening is provided on the upper portion of the power arm body; an upper maintenance opening cover is provided at the upper maintenance opening; and / or, A lower maintenance opening is provided at the lower part of the power arm body; and a lower maintenance opening cover is provided at the lower maintenance opening.

8. The cruise power module heat dissipation device according to claim 1, characterized in that: The hot air exhaust port is arranged behind the front expanded area of ​​the power arm body.

9. An aircraft cruise power module, comprising a cruise power module body, characterized in that: The cruise power module body is provided with a cruise power module heat dissipation device according to any one of claims 1 to 8.

10. An electric vertical take-off and landing aircraft, comprising an aircraft body and a cruise power module arranged on the aircraft body, characterized in that: The cruise power module is provided with a cruise power module heat dissipation device according to any one of claims 1 to 8.

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