CN214577342U

CN214577342U - Water-cooling heat abstractor for helicopter engine

Info

Publication number: CN214577342U
Application number: CN202120655153.5U
Authority: CN
Inventors: 朱悦鑫; 单伟; 刘媛媛
Original assignee: Wuxi Jinye Aviation Safety Equipment Co ltd
Current assignee: Wuxi Jinye Aviation Safety Equipment Co ltd
Priority date: 2021-03-31
Filing date: 2021-03-31
Publication date: 2021-11-02
Anticipated expiration: 2031-03-31

Abstract

The utility model discloses a water-cooling heat dissipation device for a helicopter engine, which comprises a heat extraction component and a heat exchange cladding, wherein the heat extraction component comprises two groups of fixed plates, a hollow copper pipe and a fan, the two groups of fixed plates are arranged in parallel, a plurality of groups of radiating fins are embedded and fixed between the two groups of fixed plates, one end of a rotating shaft of the fan is fixedly connected with a transmission shaft, and one end of the transmission shaft is sleeved with a gear; one group of the fixing plates are detachably provided with water circulation assemblies, the water inlets of the water circulation assemblies are communicated with one ends of the hollow copper tubes, the heat exchange cladding comprises a mounting layer, heat conduction water tubes are embedded in the mounting layer, and one ends of the heat conduction water tubes are communicated with the water outlets of the water circulation assemblies. The utility model discloses a gear drive realizes fan speed and helicopter engine rotational speed synchronous variation, realizes water-cooling radiating efficiency automatic control's effect, and simple structure is reliable.

Description

Water-cooling heat abstractor for helicopter engine

Technical Field

The utility model relates to a helicopter engine technical field specifically is a water-cooling heat abstractor for helicopter engine.

Background

The traditional helicopter adopts an air cooling mode to assist the engine in heat dissipation, and the air cooling mode is to use a duct or a fan to push unidirectional airflow to pass through an engine cylinder body to cool the engine cylinder body. The air cooling mode has the defects that: because the air flow is unidirectional, an air inlet side and an air outlet side exist, the air inlet side is high-pressure and is directly contacted with cold air, the cooling effect is relatively good, and the temperature of the engine cylinder body part close to the air inlet side is low; the air outlet side is low pressure, the air flow rate is low, and the temperature of the engine cylinder body part close to the air outlet side is high due to certain temperature rise after the air flow passes through the engine cylinder body. The defects of the air cooling mode in the aspect of heat dissipation effect cause the temperature of an engine cylinder body to be unbalanced, damage is caused to the engine, and the service life of the engine is shortened.

At present, a part of helicopters use cold water to radiate the engine, but most of the existing water-cooling radiating devices for the helicopter engine adopt independent radiating devices, the water-cooling radiating mechanism is integrally independent and does not interact with a helicopter engine system, the power of water-cooling radiation is completely automatically and manually regulated, a user is difficult to accurately regulate the radiating efficiency, and poor radiating effect or energy waste is easily caused; some water-cooling heat dissipation devices for helicopter engines adopt sensors and controllers to form an automatic control heat dissipation regulating system, but the mode is high in cost and easy to break down to influence the heat dissipation of the engine, so that the water-cooling heat dissipation device for helicopter engines needs to be provided.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a water-cooling heat abstractor for helicopter engine through gear drive, realizes fan speed and helicopter engine speed synchronous variation, realizes water-cooling heat dissipation efficiency automatic control's effect, and simple structure is reliable to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: a water-cooling heat dissipation device for a helicopter engine comprises a heat dissipation component and a heat exchange cladding, wherein the heat dissipation component comprises two groups of fixing plates, a hollow copper pipe and a fan, the two groups of fixing plates are arranged in parallel, the two groups of fixing plates are fixedly connected through a connecting rod, a plurality of groups of cooling fins are embedded and fixed between the two groups of fixing plates and are arranged at equal intervals, the hollow copper pipe is embedded in the plurality of groups of cooling fins, two ends of the fan are fixedly arranged on the side edges of the two groups of fixing plates through screws respectively, one end of a rotating shaft of the fan is fixedly connected with a transmission shaft, and one end of the transmission shaft is sleeved with a gear;

one group of the fixing plates are detachably provided with water circulation assemblies, the water inlets of the water circulation assemblies are communicated with one ends of the hollow copper pipes, the heat exchange cladding comprises an installation layer, heat conduction water pipes are embedded in the installation layer, one ends of the heat conduction water pipes are communicated with the water outlets of the water circulation assemblies, and the other ends of the hollow copper pipes are communicated with the other ends of the heat conduction water pipes.

Preferably, the hollow copper pipe is arranged in a U shape, and the two ends of the hollow copper pipe are both penetrated through fixing plates provided with water circulation assemblies.

Preferably, one of the fixing plates is provided with an air exhaust hole, the air exhaust hole and the water circulation assembly are respectively located on the two groups of fixing plates, the radiating fins are provided with a plurality of groups of radiating holes, and the plurality of groups of radiating holes are arranged in an equidistant array.

Preferably, the water circulation assembly comprises a water tank and a water pump, the water pump is fixedly mounted at the upper end of the water tank, the water tank is detachably mounted on one group of fixing plates, a water inlet of the water pump is communicated with the water tank, the water tank is communicated with one end of the hollow copper pipe, and a water outlet of the water pump is communicated with one end of the heat conducting water pipe.

Preferably, two sets of tube inserting holes are formed in the lower end of the water tank, two ends of the hollow copper tube are respectively inserted into the two sets of tube inserting holes, the other end of the heat conducting water tube is fixedly connected and communicated with an intermediate water tube, one end of the intermediate water tube is inserted into the water tank, and one end of the intermediate water tube is fixedly connected and communicated with the other end of the hollow copper tube.

Preferably, one side of keeping away from middle water pipe on the installation layer is fixedly installed with heat conduction and pastes the layer, heat conduction pastes layer elasticity silicone grease and pastes the layer.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model discloses a fan is installed between two sets of fixed plates, and the one end of fan pivot cup joints the design of gear through the transmission shaft for through gear drive, make helicopter engine drive the fan through gear drive when rotating and rotate, thereby make fan rotational speed and helicopter engine rotational speed synchronous variation, realize water-cooling radiating efficiency automatic control's effect, simple structure is reliable, and the practicality is strong.

Drawings

Fig. 1 is a schematic structural view of the present invention;

fig. 2 is a schematic view of the heat removal assembly of the present invention;

FIG. 3 is a schematic view of the air outlet of the present invention;

FIG. 4 is a schematic view of the water tank of the present invention;

FIG. 5 is a schematic view of the internal structure of the water tank of the present invention;

fig. 6 is a schematic view of the hollow copper tube of the present invention.

In the figure: 1. a heat removal assembly; 101. a fixing plate; 102. a hollow copper tube; 103. a connecting rod; 104. a heat sink; 105. a fan; 106. a drive shaft; 107. a gear; 108. an air exhaust hole; 2. a water circulation assembly; 21. a water tank; 22. a water pump; 212. a cannula hole; 3. heat exchange cladding; 31. mounting a layer; 32. a heat conducting water pipe; 33. a heat conducting adhesive layer; 4. a middle water pipe.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-6, the present invention provides a technical solution: a water-cooling heat dissipation device for a helicopter engine comprises a heat dissipation component 1 and a heat exchange cladding 3, wherein the heat dissipation component 1 comprises two groups of fixing plates 101, hollow copper tubes 102 and fans 105, the two groups of fixing plates 101 are arranged in parallel, the two groups of fixing plates 101 are fixedly connected through connecting rods 103, a plurality of groups of radiating fins 104 are fixedly embedded between the two groups of fixing plates 101, the plurality of groups of radiating fins 104 are arranged at equal intervals, the hollow copper tubes 102 are embedded in the plurality of groups of radiating fins 104, the hollow copper tubes 102 are arranged in a U shape, and two ends of the hollow copper tubes 102 are respectively provided with the fixing plates 101 of a water circulation component 2 in a penetrating mode;

wherein, the air outlet 108 is arranged on one group of the fixed plates 101, the air outlet 108 and the water circulation component 2 are respectively positioned on the two groups of the fixed plates 101, the heat sink 104 is provided with a plurality of groups of heat dissipation holes, and the plurality of groups of heat dissipation holes are arranged in an equidistant array; the other group of fixing plates 101 are detachably provided with a water circulation assembly 2, and a water inlet of the water circulation assembly 2 is communicated with one end of the hollow copper pipe 102;

the water circulation assembly 2 comprises a water tank 21 and a water pump 22, the water pump 22 is fixedly arranged at the upper end of the water tank 21, the water tank 21 is detachably arranged on one group of fixing plates 101, a water inlet of the water pump 22 is communicated with the water tank 21, the water tank 21 is communicated with one end of a hollow copper pipe 102, and a water outlet of the water pump 22 is communicated with one end of a heat conduction water pipe 32;

a water flow loop is formed by the water pump 22, the hollow copper pipe 102 and the heat conducting water pipe 32, so that water forms circulation, when reaching the heat conducting water pipe 32, the heat of the engine is taken away, and the effect of automatically controlling the water cooling heat dissipation efficiency is achieved.

The heat exchange cladding 3 comprises an installation layer 31, a heat conduction water pipe 32 is embedded in the installation layer 31, one end of the heat conduction water pipe 32 is communicated with a water outlet of the water circulation assembly 2, the other end of the hollow copper pipe 102 is communicated with the other end of the heat conduction water pipe 32, a heat conduction adhesive layer 33 is fixedly installed on one side, far away from the middle water pipe 4, of the installation layer 31, and an elastic silicone grease adhesive layer is arranged on the heat conduction adhesive layer 33; during the use, with heat transfer cladding 3 fixed mounting in helicopter engine' S surface for heat conduction adhesive layer 33 and helicopter engine laminating, the big or small shape of heat transfer cladding 3 can be makeed according to the size of engine, and heat conduction water pipe 32 is the S-shaped and sets up in installation layer 31, and installation layer 31 and heat conduction water pipe 32 all set up to the copper product.

Two sets of tube inserting holes 212 are opened to the lower extreme of water tank 21, and peg graft respectively in two sets of tube inserting holes 212 at the both ends of hollow copper pipe 102, and the other end fixed connection of heat conduction water pipe 32 and intercommunication have middle water pipe 4, and the one end of middle water pipe 4 is pegged graft in water tank 21, and the one end of middle water pipe 4 and the other end fixed connection and the intercommunication of hollow copper pipe 102.

Two ends of the fan 105 are respectively and fixedly installed on the side edges of the two groups of fixing plates 101 through screws, one end of a rotating shaft of the fan 105 is fixedly connected with a transmission shaft 106, and one end of the transmission shaft 106 is sleeved with a gear 107.

When the heat exchange device is used, the heat exchange cladding 3 is fixedly arranged on the surface of a helicopter engine, the heat conduction adhesive layer 33 is attached to the helicopter engine, the transmission gear is sleeved on an output shaft of the helicopter engine and is meshed with the gear 107, after the engine is started, the gear drives the fan to rotate, so that the rotating speed of the fan and the rotating speed of the helicopter engine synchronously change, the water pump 22 is opened at the moment to enable water in the hollow copper tube 102 to form circulation, and when the water reaches the heat conduction water tube 32, the heat of the engine is taken away, so that the effect of automatically controlling the water cooling heat dissipation efficiency is realized.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a water-cooling heat abstractor for helicopter engine, includes heat extraction subassembly (1) and heat transfer cladding (3), its characterized in that: the heat extraction assembly (1) comprises two groups of fixing plates (101), a hollow copper tube (102) and a fan (105), wherein the two groups of fixing plates (101) are arranged in parallel, the two groups of fixing plates (101) are fixedly connected through a connecting rod (103), a plurality of groups of radiating fins (104) are fixedly embedded between the two groups of fixing plates (101), the plurality of groups of radiating fins (104) are arranged at equal intervals, the hollow copper tube (102) is embedded in the plurality of groups of radiating fins (104), two ends of the fan (105) are fixedly arranged on the side edges of the two groups of fixing plates (101) through screws respectively, one end of a rotating shaft of the fan (105) is fixedly connected with a transmission shaft (106), and one end of the transmission shaft (106) is sleeved with a gear (107);

one group of the fixing plates (101) are detachably provided with water circulation assemblies (2), water inlets of the water circulation assemblies (2) are communicated with one ends of hollow copper pipes (102), the heat exchange cladding (3) comprises an installation layer (31), heat conduction water pipes (32) are embedded in the installation layer (31), one ends of the heat conduction water pipes (32) are communicated with water outlets of the water circulation assemblies (2), and the other ends of the hollow copper pipes (102) are communicated with the other ends of the heat conduction water pipes (32).

2. A water-cooled heat sink for a helicopter engine as defined in claim 1, wherein: the hollow copper pipe (102) is arranged in a U shape, and two ends of the hollow copper pipe (102) are both penetrated through the fixing plates (101) provided with the water circulation assemblies (2).

3. A water-cooled heat sink for a helicopter engine as defined in claim 2, wherein: wherein set up exhaust hole (108) on a set of fixed plate (101), exhaust hole (108) and hydrologic cycle subassembly (2) are located two sets of fixed plates (101) respectively, seted up multiunit louvre on fin (104), and multiunit louvre equidistance array sets up.

4. A water-cooled heat sink for a helicopter engine as defined in claim 3, wherein: the water circulation assembly (2) comprises a water tank (21) and a water pump (22), the water pump (22) is fixedly installed at the upper end of the water tank (21), the water tank (21) is fixedly installed on one group of fixing plates (101) through screws, a water inlet of the water pump (22) is communicated with the water tank (21), the water tank (21) is communicated with one end of a hollow copper pipe (102), and a water outlet of the water pump (22) is communicated with one end of a heat conduction water pipe (32).

5. The water-cooled heat sink for a helicopter engine as recited in claim 4, further comprising: two groups of insertion tube holes (212) are formed in the lower end of the water tank (21), two ends of the hollow copper tube (102) are respectively inserted into the two groups of insertion tube holes (212), the other end of the heat conduction water tube (32) is fixedly connected and communicated with the middle water tube (4), one end of the middle water tube (4) is inserted into the water tank (21), and one end of the middle water tube (4) is fixedly connected and communicated with the other end of the hollow copper tube (102).

6. A water-cooled heat sink for a helicopter engine as defined in claim 5, wherein: one side fixed mounting who keeps away from middle water pipe (4) on installation layer (31) has heat conduction pad pasting layer (33), heat conduction pad pasting layer (33) elasticity silicone grease pastes the layer.