阅读说明：本技术 飞机发动机的散热装置以及交叉双旋翼无人直升机 (Heat dissipation device of aircraft engine and cross double-rotor unmanned helicopter ) 是由 王贤宇 印明威 海日汗 包长春 徐震翰 李京阳 于 2021-02-01 设计创作，主要内容包括：本发明公开了一种飞机发动机的散热装置以及交叉双旋翼无人直升机。散热装置包括：第一散热器、第二散热器和连接组件；第一散热器包括：与飞机发动机的水冷系统连通的第一流通部以及向第一流通部引风的第一引风部；第二散热器包括：用与飞机发动机的滑油系统连通的第二流通部以及向第二流通部引风的第二引风部；第一散热器布置在第二散热器上方,并与第二散热器集成为一体式散热单元；一体式散热单元具有外壁部,连接组件固定于外壁部,连接组件与飞机发动机的机架固定连接。该散热装置能同时对飞机发动机的水冷系统和滑油系统进行冷却,具有较高的散热效率,满足散热需求,并且零部件数量少,结构紧凑,满足小空间布置需求。(The invention discloses a heat dissipation device of an aircraft engine and a cross double-rotor unmanned helicopter. The heat dissipating double-fuselage includes: the first radiator, the second radiator and the connecting component; the first heat sink includes: the first circulation part is communicated with a water cooling system of the aircraft engine, and the first air inducing part induces air to the first circulation part; the second heat sink includes: a second flow-through portion communicating with a lubricating oil system of the aircraft engine and a second air-inducing portion inducing air to the second flow-through portion; the first radiator is arranged above the second radiator and integrated with the second radiator into an integrated radiating unit; the integrated heat dissipation unit is provided with an outer wall part, the connecting assembly is fixed on the outer wall part, and the connecting assembly is fixedly connected with a frame of the aircraft engine. The heat dissipation device can cool the water cooling system and the lubricating oil system of the aircraft engine at the same time, has higher heat dissipation efficiency, meets the heat dissipation requirement, has small quantity of parts and compact structure, and meets the requirement of small-space arrangement.)

1. Heat sink for an aircraft engine, characterized in that it comprises a first radiator (10), a second radiator (20) and a connecting assembly (31, 32);

the first heat sink (10) comprises: the water cooling system comprises a first circulation part used for being communicated with a water cooling system of an aircraft engine and a first air inducing part used for inducing air to the first circulation part;

the second heat sink (20) includes: a second flow-through for communicating with an oil system of an aircraft engine, and a second wind-inducing portion for inducing wind to the second flow-through;

the first radiator (10) is arranged above the second radiator (20) and is integrated with the second radiator (20) into an integrated radiating unit;

the integrated heat dissipation unit is provided with an outer wall part, and the connecting assemblies (31, 32) are fixedly connected to the outer wall part and used for connecting a frame of an aircraft engine.

2. The aircraft engine heat sink as recited in claim 1, wherein the integral heat sink unit is a trapezoidal structure having a wide top and a narrow bottom.

3. An aircraft engine heat sink as defined in claim 1, wherein the outer wall portion comprises a peripheral wall portion and an end wall portion (b); the peripheral wall part comprises a top wall (a1), a left side wall (a2), a bottom wall (a3) and a right side wall (a4) which are connected end to end, and the end wall part (b) is connected to the front end or the rear end of the peripheral wall part and is positioned in the enclosed space of the peripheral wall part; a partition plate (c) is arranged in the enclosed space of the peripheral wall part, the partition plate (c) divides the enclosed space of the peripheral wall part into an upper chamber and a lower chamber, the first air inducing part is arranged in the upper chamber, and the second air inducing part is arranged in the lower chamber.

4. The aircraft engine heat sink as recited in claim 3, characterised in that the first flow-through comprises a first core (11), the second flow-through comprises a second core (21), the first core (11) and the second core (21) comprise heat exchange tubes and fins, the first core (11) is arranged in the upper chamber, and the second core (21) is arranged in the lower chamber.

5. The heat sink for an aircraft engine according to claim 4, characterized in that the first flow-through portion further includes a left water chamber (12) and a right water chamber (13) which are respectively disposed on the left and right sides of the first core (11) and communicate with the first core (11); the second flow-through portion further includes a left oil chamber (22) and a right oil chamber (23) which are respectively disposed on the left and right sides of the second core (21) and communicate with the second core (21); the left water chamber (12), the right water chamber (13), the left oil chamber (22) and the right oil chamber (23) are formed by enclosing the peripheral wall part, the partition plate (c), the end wall part (b) and the baffle plate (d).

6. The heat dissipation device of an aircraft engine according to claim 5, wherein the first circulation portion further includes a water inlet connection pipe (14) communicating with one water chamber and a water outlet connection pipe (15) communicating with the other water chamber, the second circulation portion further includes a water inlet connection pipe (24) communicating with one oil chamber and an oil outlet connection pipe (25) communicating with the other oil chamber, and the water inlet connection pipe (14), the water outlet connection pipe (15), the water inlet connection pipe (24) and the oil outlet connection pipe (25) are connected to the front end of the water chamber or the oil chamber; the water inlet connecting pipe (14) and the water outlet connecting pipe (15) are arranged in a vertically staggered manner; and a flow surrounding plate is arranged in the left water chamber (12) and/or the right water chamber (13).

7. The heat sink for an aircraft engine according to any one of claims 1 to 6, wherein the first air induction portion and the second air induction portion comprise a cylindrical body and a blade arranged in the cylindrical body, the cylindrical body (16) of the first air induction portion is entirely circumferentially abutted against the rear end of the first flow portion and fixedly connected with the first flow portion, and the cylindrical body (26) of the second air induction portion is entirely circumferentially abutted against the rear end of the second flow portion and fixedly connected with the second flow portion.

8. The aircraft engine heat sink according to any one of claims 3 to 6, wherein the connecting assembly is an ear plate assembly, the ear plate assembly comprises an L-shaped ear plate (31) and a flat ear plate (32), the transverse portion of the L-shaped ear plate (31) is fixedly connected to the top wall (a1) of the integrated heat dissipating unit, the flat ear plate (32) is fixedly connected to the end wall (b) of the integrated heat dissipating unit, and the longitudinal portion of the L-shaped ear plate (31) and the flat ear plate (32) are fixedly connected to the frame of the aircraft engine through the ear hole thereon and a threaded fastener penetrating through the ear hole.

9. A cross twin rotor unmanned helicopter comprising a heat sink, wherein the heat sink is as claimed in any one of claims 1 to 8, and is secured between the frame of the aircraft engine and the aircraft skin.

10. An aircraft engine heat sink as defined in claim 9, wherein the direction of wind induction of the first and second wind-guiding portions of the heat sink is aligned with the direction of the oncoming airflow of the aircraft.

Technical Field

The invention relates to the technical field of heat dissipation of aircraft engines, in particular to a heat dissipation device of an aircraft engine and a cross double-rotor unmanned helicopter adopting the heat dissipation device.

Background

The unmanned helicopter has wider and more popular application and has penetrated into various fields of national life. The engine is the heart of the unmanned helicopter, plays an important role in the reliability, safety and the like of the operation of the unmanned helicopter, and needs to be provided with a heat dissipation device in order to ensure the stable operation of the engine.

The cross double-rotor unmanned helicopter is one of unmanned helicopters, and has the advantages of good stability, strong load-carrying capacity and the like, so that the cross double-rotor unmanned helicopter is widely applied. The design requirement of the cross dual-rotor unmanned helicopter is as follows: the structure layout is compact, so the arrangement space left for the heat dissipation device is very limited, and the small space has higher requirements on the heat dissipation performance of the heat dissipation device.

Therefore, how to mount the heat dissipation device in a limited space and make the heat dissipation device have excellent heat dissipation capability for the heat dissipation device of the cross twin-rotor unmanned helicopter is a technical problem to be solved by those skilled in the art.

Disclosure of Invention

In order to solve the above technical problem, the present invention provides a heat dissipation device for an aircraft engine, comprising: the first radiator, the second radiator and the connecting component;

the first heat sink includes: the water cooling system comprises a first circulation part used for being communicated with a water cooling system of an aircraft engine and a first air inducing part used for inducing air to the first circulation part;

the second heat sink includes: a second flow-through for communicating with an oil system of an aircraft engine, and a second wind-inducing portion for inducing wind to the second flow-through;

the first radiator is arranged above the second radiator and integrated with the second radiator into an integrated radiating unit;

the integrated heat dissipation unit is provided with an outer wall portion, the connecting assembly is fixed on the outer wall portion, and the connecting assembly is used for connecting a frame of an aircraft engine.

In one embodiment, the integral heat dissipation unit is a trapezoid structure with a wide top and a narrow bottom.

In one embodiment, the outer wall portion includes a peripheral wall portion and an end wall portion; the peripheral wall part comprises a top wall, a left side wall, a bottom wall and a right side wall which are sequentially connected end to end, and the end wall part is connected to the front end or the rear end of the peripheral wall part and is positioned in the enclosed space of the peripheral wall part; the partition board is arranged in the enclosed space of the peripheral wall part and divides the enclosed space of the peripheral wall part into an upper chamber and a lower chamber, the first air inducing part is arranged in the upper chamber, and the second air inducing part is arranged in the lower chamber.

In one embodiment, the first flow through portion includes a first core, the second heat sink includes a second core, the first core and the second core include heat exchange tubes and fins, the first core is disposed in the upper chamber, and the second core is disposed in the lower chamber.

In one embodiment, the first circulating part further includes a left water chamber and a right water chamber which are respectively disposed at left and right sides of the first core and communicate with the first core; the second circulation portion further includes a left oil chamber and a right oil chamber which are respectively disposed on left and right sides of the second core and communicate with the second core; the left water chamber and the left oil chamber are formed by enclosing the top wall, the left side wall, the end wall part, the partition plate and the baffle plate which is arranged opposite to the left side wall; the right water chamber and the right oil chamber are formed by enclosing the top wall, the right side wall, the end wall part, the partition plate and the baffle plate oppositely arranged with the right side wall.

In one embodiment, the first circulation portion further includes a water inlet connection pipe communicated with one water chamber and a water outlet connection pipe communicated with the other water chamber, the second circulation portion further includes a water inlet connection pipe communicated with one oil chamber and an oil outlet connection pipe communicated with the other oil chamber, and the water inlet connection pipe, the water outlet connection pipe, the water inlet connection pipe and the oil outlet connection pipe are connected to the front end of the water chamber or the oil chamber; the water inlet connecting pipe and the water outlet connecting pipe are arranged in a vertically staggered manner; and the left water chamber and the right water chamber are internally provided with a flow surrounding plate.

In one embodiment, the first air inducing portion and the second air inducing portion include a cylinder and a blade arranged in the cylinder, the cylinder front end of the first air inducing portion abuts against the rear end of the first flow portion and is fixedly connected with the first flow portion, and the cylinder front end of the second air inducing portion abuts against the rear end of the second flow portion and is fixedly connected with the second flow portion.

In an embodiment, the connecting portion adopt the otic placode subassembly, the otic placode subassembly includes L shape otic placode and flat otic placode, the horizontal portion of L shape otic placode link firmly in the perisporium portion of integral type radiating element, the flat otic placode link firmly in the end wall portion of integral type radiating element, the vertical portion of L shape otic placode and the flat otic placode through the earhole on it and wear in the threaded fastener of earhole and aircraft engine's frame fixed connection.

In addition, the invention also provides a cross double-rotor unmanned helicopter which comprises a heat dissipation device, wherein the heat dissipation device adopts any one of the heat dissipation devices, and the heat dissipation device is fixed between a frame of an aircraft engine and an aircraft skin.

In one embodiment, the direction of air induction of the first and second air induction portions of the heat sink is aligned with the direction of the oncoming airflow of the aircraft.

The technical effects are as follows: according to the heat dissipation device provided by the invention, the first radiator 10 and the second radiator are arranged, so that not only can a water cooling system of an aircraft engine be cooled, but also a lubricating oil system of the aircraft engine can be cooled, and forced convection heat dissipation can be formed on the first circulation part and the second circulation part by arranging the air guide part, so that the heat dissipation effect is ensured. Meanwhile, the first radiator and the second radiator are integrated together to form the integrated radiating unit, and the integrated radiating unit is connected with the frame of the aircraft engine through the connecting assembly fixed on the integrated radiating unit, so that the two radiators are prevented from being installed independently, the number of parts is reduced, and the requirement of small-space arrangement is met.

Drawings

Fig. 1 is a front view of an embodiment of a heat dissipation device provided in the present invention;

fig. 2 is a right side view of fig. 1.

The reference numerals are explained below:

10 a first radiator, 11 a first core, 12 a left water chamber, 13 a right water chamber, 14 a water inlet connecting pipe, 15 a water outlet connecting pipe and 16 a cylinder body of a first induced draft part;

20 a second radiator, 21 a second core body, 22 a left oil chamber, 23 a right oil chamber, 24 an oil inlet connecting pipe orifice, 25 an oil outlet connecting pipe and 26 a cylinder body of a second air inducing part;

a1 top wall, a2 left side wall, a3 bottom wall, a4 right side wall;

b an end wall portion;

c, a partition board;

d, a baffle plate;

31L-shaped ear plates, 32 flat ear plates;

4 connecting pieces.

Detailed Description

In order to make those skilled in the art better understand the technical solution of the present invention, the technical solution of the present invention is further described in detail below with reference to the accompanying drawings and the detailed description.

The heat dissipating device in the illustrated embodiment includes a first heat sink 10, a second heat sink 20, and a connecting assembly.

The first heat sink 10 includes a first flow-through portion and a first air-inducing portion. In the application state, the first circulation part is communicated with a water cooling system of the aircraft engine. The first air inducing portion induces the air flow to the first circulating portion, so that the first heat sink 10 convects heat by air and water.

The second heat sink 20 includes a second flow portion and a second wind-guiding portion. In the application state, the second flow-through part is communicated with a lubricating oil system of the aircraft engine. The second air inducing portion induces the air flow to the second circulating portion, so that the second radiator 20 performs heat convection by using the air and the oil.

The first heat sink 10 is disposed above the second heat sink 20, and is integrated with the second heat sink 20 into an integrated heat dissipation unit. The integrated heat dissipation unit includes an outer wall portion including a peripheral wall portion and an end wall portion b. The peripheral wall portion includes a top wall a1, a left side wall a2, a bottom wall a3, and a right side wall a4, which are connected end to end in this order. The end wall portion b is connected to the front end or the rear end of the peripheral wall portion and is located in the enclosed space of the peripheral wall portion.

The connecting component is fixedly connected to the outer wall part. The connecting assembly may be an ear plate assembly. The ear plate assembly comprises L-shaped ear plates 31 and flat ear plates 32, two L-shaped ear plates 31 and two flat ear plates 32 being shown.

The transverse portion of the L-shaped ear plate 31 is fixed to the top wall a1, and the flat ear plate 32 is fixed to the end wall b, which may be welded or screwed. The L-shaped ear plate 31 is provided with ear holes at the longitudinal part and the flat ear plate 32. In the application state, the longitudinal part of the L-shaped lug plate 31 and the flat lug plate 32 are fixedly connected with the frame of the aircraft engine through lug holes on the L-shaped lug plate and threaded fasteners penetrating through the lug holes. It should be noted that the connecting assembly is not limited to the ear plate assembly, and for example, a snap assembly may be used.

The connecting component adopts the lug plate component, and has the advantages that: the connection operation is convenient, the connection reliability is high, and particularly, the L-shaped lug plate 31 and the flat lug plate 32 are matched for use, so that the connection reliability is higher.

The heat dissipation device can cool a water cooling system of an aircraft engine and can also cool an oil lubricating system of the aircraft engine by arranging the first radiator 10 and the second radiator 20, and forced convection heat dissipation can be formed on the first circulation part and the second circulation part by arranging the air inducing part, so that the heat dissipation effect is guaranteed. Meanwhile, the first radiator 10 and the second radiator 20 are integrated together to form an integrated radiating unit, and the integrated radiating unit is connected with a frame of an aircraft engine through a connecting assembly fixed on the integrated radiating unit, so that the two radiators are prevented from being independently installed, the number of parts is reduced, and the requirement of small-space arrangement is met.

The heat dissipation device has the advantages that: the small-space arrangement requirement can be met, and the heat dissipation device has a good heat dissipation effect and high heat dissipation efficiency.

Specifically, the distance between the lower end of the left side wall a2 and the lower end of the right side wall a4 is smaller than the distance between the upper end of the left side wall a2 and the upper end of the right side wall a4, the top wall a1 is connected between the upper end of the left side wall a2 and the upper end of the right side wall a4, and the bottom wall a3 is connected between the lower end of the left side wall a2 and the lower end of the right side wall a4, so that the integral heat dissipation unit is of a trapezoidal structure with a wide top and a narrow bottom. The structure is more beneficial to saving the arrangement space, and the integral heat dissipation capacity of the integrated heat dissipation unit can be ensured to meet the requirement.

Specifically, a partition plate c is arranged in a surrounding space of a surrounding wall portion of the integrated heat dissipation unit, and the surrounding space of the surrounding wall portion is divided into an upper chamber and a lower chamber by the partition plate c. The first flow-through portion includes a first core 11, the second flow-through portion includes a second core 21, the first core 11 and the first induced draft portion are disposed in the upper chamber, and the second core 21 and the second induced draft portion are disposed in the lower chamber. The first core 11 and the second core 21 include heat exchange tubes and heat exchange fins.

Specifically, the first circulating part further includes a left water chamber 12, a right water chamber 13, a water inlet connection pipe 14 and a water outlet connection pipe 15. The left water chamber 12 is disposed at the left side of the first core 11, and communicates with the heat exchange tubes of the first core 11. The right water chamber 13 is disposed at the right side of the first core 11, and communicates with the heat exchange tubes of the first core 11. The left water chamber 12 is surrounded by a top wall a1, a left side wall a2, a partition c, an end wall b, and a baffle d disposed opposite the left side wall a 2. The right water chamber 13 is surrounded by a top wall a1, a right side wall a4, a partition c, an end wall b, and a baffle d disposed opposite to the right side wall a 4. The end wall part b of the front ends of the left water chamber 12 and the right water chamber 13 is provided with a communicating hole, a water inlet connecting pipe 14 is connected with the communicating hole of the left water chamber 12, and a water outlet connecting pipe 15 is connected with the communicating hole of the right water chamber 13.

In the illustrated embodiment, the communication hole of the left water chamber 12 is formed at the upper portion of the left water chamber 12, the communication hole of the right water chamber 13 is formed at the upper portion of the right water chamber 13, and the water inlet connection pipe 14 and the water outlet connection pipe 15 are arranged in a vertically staggered manner, so that water flow can be promoted by using pressure difference, and heat dissipation efficiency can be further improved. In addition, a flow-around plate may be disposed inside the left water chamber 12 and/or the right water chamber 13, and the flow-around plate may enhance turbulence, thereby further improving heat dissipation efficiency.

Specifically, the second circulation portion further includes a left oil chamber 22, a right oil chamber 23, an oil inlet connection pipe 24, and an oil outlet connection pipe 25. The left oil chamber 22 is disposed on the left side of the second core 21, communicating with the heat exchange tubes of the second core 21. The right oil chamber 23 is disposed on the right side of the second core 21, communicating with the heat exchange tubes of the second core 21. The left oil chamber 22 is surrounded by a bottom wall a3, a left side wall a2, a partition plate c, an end wall b, and a baffle plate d provided opposite to the left side wall a 2. The right oil chamber 23 is surrounded by a bottom wall a3, a right side wall a4, a partition plate c, an end wall b, and a baffle plate d provided opposite to the right side wall a 4. The end wall part b at the front ends of the left oil chamber 22 and the right oil chamber 23 is provided with a communicating hole, an oil inlet connecting pipe 24 is connected with the communicating hole of the left oil chamber 22, and an oil outlet connecting pipe 25 is connected with the communicating hole of the right oil chamber 23.

Specifically, each of the first and second air guiding portions includes a cylinder, a blade (not shown) disposed in the cylinder, and a motor for driving the blade to rotate. In the application state, the motor is conductively connected with a power supply part of the aircraft engine.

The barrel 16 front end of first induced air portion is fixed in first circulation portion, and the whole week of front end all offsets with first circulation portion, the barrel 26 front end of second induced air portion is fixed in second circulation portion, and the whole week of front end all offsets with second circulation portion, set up like this, the barrel 16 of first induced air portion encloses jointly with first circulation portion and closes formation relatively confined space, the barrel 26 of second induced air portion and second circulation portion enclose jointly and close formation relatively confined space, thereby can reduce the loss of induced air portion amount of wind, make the induced air portion bleed basically all flow through circulation portion, consequently, can further promote the radiating efficiency.

In the scheme shown in the figure, the front end of the cylinder 16 of the first air guiding part is connected with the first core 11 through a connecting sheet and a threaded fastener penetrating through the connecting sheet, and a plurality of connecting sheets 4 (four in the figure) are sequentially arranged at equal intervals along the circumferential direction of the front end, so that the connection reliability and the relative sealing property after connection are ensured. Similarly, the front end of the cylinder 26 of the second air guiding part is connected with the second core body 21 through a connecting piece and a threaded fastener penetrating through the connecting piece, and a plurality of connecting pieces 4 (four in the figure) are sequentially arranged at equal intervals along the circumferential direction of the front end, so that the connection reliability and the relative sealing performance after the connection is finished can be ensured.

The heat dissipation device can be applied to the cross twin-rotor unmanned helicopter, and when the heat dissipation device is applied to the cross twin-rotor unmanned helicopter, the heat dissipation device is fixed between a frame of an aircraft engine and an aircraft skin.

Specifically, can make first induced air portion and second induced air portion from preceding back induced air through the shape and the installation angle of the blade of first induced air portion of rational design and second induced air portion, when installing it on the unmanned helicopter of alternately two rotors, can let heat abstractor's front end towards the aircraft nose, like this, the induced air direction of induced air portion can be unanimous with the air current direction of the incoming of aircraft to this induced air volume that can promote induced air portion, thereby can further promote the radiating efficiency.

The air inducing device of the aircraft engine and the cross double-rotor unmanned helicopter provided by the invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.