CN102295072A - Single-layer air-liquid aircraft skin heat exchange method - Google Patents

Abstract

The invention relates to an aircraft single-layer air-liquid skin heat exchange method, which belongs to the technical field of environmental control, is a new technology for reducing the air volume of an aircraft ram, and improves the air-liquid heat exchange efficiency, and is an improvement to the air-liquid heat exchange mode. A single-layer air-liquid skin heat exchanger is installed on the outer surface of the fuselage, and the air-liquid skin heat exchanger includes an outer surface (1), an inner surface (2), a liquid inlet (3), and a liquid outlet ( 4), seal the ends (5), (6), and the connection part (8) with the fuselage, and install a single-layer cooling fin (7) between the outer surface (1) and the inner surface (2). Compared with the air-air skin heat exchanger, this method has higher heat transfer coefficient, larger heat transfer, and better cooling effect; compared with the air-liquid heat exchanger, the air-liquid skin heat exchanger Utilizing the boundary layer heat dissipation technology integrated with the aircraft skin, the traditional ram intake air cooling method is cancelled, which greatly reduces the system’s fuel compensation loss to the aircraft and improves the flight time of the aircraft; at the same time, it can meet the requirements of the aircraft. Stealth performance requirements.

Description

A heat exchange method for aircraft single-layer air-liquid skin

technical field

The invention belongs to the technical field of environment control and is an improvement to the air-liquid heat exchange mode.

Background technique

At present, there are two kinds of technologies close to this patent in the environmental control system at home and abroad:

1) Air-liquid heat exchanger (abbreviation: air-liquid heat exchanger) - use ram air inlet to cool the thermal fluid from electronic equipment. At present, most aircrafts at home and abroad adopt this form .

Advantages: The air-liquid heat exchanger and the ram air intake are simple in design and easy to coordinate and install on the aircraft.

Disadvantages: The air-liquid heat exchanger has a large volume and a high height (usually greater than 100mm), and the ram air intake and ram air have a large aerodynamic resistance on the aircraft, and the air in the ram air intake has a large fuel load on the aircraft compensatory loss.

2) Air-air skin heat exchanger (abbreviation: air skin heat exchanger) - when hot air flows in the interlayer between the outer skin of the aircraft and the fuselage structure, the relative velocity of the aircraft and the ambient air is used to The hot air is used for cooling down, which is currently used by aircraft, such as A320, B767, and C-17; patents close to this invention include: Airbus 200780009653.4 "exhaust device, aircraft and used to make the exterior of the aircraft method of fluid outflow between the inner lining panels of the skin".

Advantages: The air-skin heat exchanger is located on the inner surface of the aircraft skin, which has small aerodynamic resistance to the aircraft and relatively small fuel compensation loss; in addition, since the air-skin heat exchanger is installed inside the aircraft, the heat flowing in the heat exchanger It is air, so the air skin heat exchanger does not have high requirements on its own airtightness.

Disadvantages: The heat exchange capacity and cooling effect of the air-air skin heat exchanger are far inferior to the air-liquid skin heat exchanger (referred to as: liquid skin heat exchanger), and the liquid flows in the liquid skin heat exchanger. Such as No. 65 coolant, etc.

Contents of the invention

The purpose of the invention is: through the technical scheme of the invention, the aerodynamic resistance and fuel compensation loss of the aircraft can be reduced, the endurance time of the aircraft can be prolonged, and at the same time, the stealth performance requirement of the aircraft can be met.

Technical scheme of the present invention is:

An aircraft single-layer air-liquid skin heat exchange method is characterized in that a single-layer air-liquid skin heat exchanger is installed on the outer surface of the fuselage, and the air-liquid skin heat exchanger includes an outer surface and an inner surface , the liquid inlet, the liquid outlet, the sealing end, and the part connected with the fuselage, and a single-layer cooling fin is installed between the outer surface and the inner surface.

The air-liquid skin heat exchanger is attached to the outer surface of the fuselage skin, and the outer surface of the fuselage skin and the air-liquid skin heat exchanger are connected by screw connection or airtight screw connection.

Part of the skin is removed from the outer surface of the fuselage, and an air-liquid skin heat exchanger is embedded, and the outer surface of the fuselage and the air-liquid skin heat exchanger are connected by screw connection or airtight screw connection.

The material used for the air-liquid skin heat exchanger is aluminum alloy.

The beneficial effects of the present invention are: compared with the air-air skin heat exchanger, the method has higher heat transfer coefficient, larger heat transfer, and better refrigeration effect; Compared with the liquid heat exchanger, the air-liquid skin heat exchanger uses the boundary layer heat dissipation technology integrated with the aircraft skin, cancels the traditional ram intake air cooling method, and greatly reduces the impact of the system on the aircraft. Compensation loss of fuel oil improves the flight time of the aircraft; at the same time, it can meet the stealth performance requirements of the aircraft.

Taking a certain type of aircraft as an example, the thermal load of electronic equipment is 13kW, the flight time is 4h, and the aircraft is flying at cruising altitude. If an air-liquid skin heat exchanger is used instead of an air-liquid heat When the ram air volume is 2160kg/h, it can reduce the compensatory loss of aircraft fuel by 307kg, and extend the flight time by 10 minutes (the extended flight time includes the flight time increased by canceling the ram inlet drum to reduce the aerodynamic resistance of the aircraft). The overall dimensions of the air-liquid heat exchanger above are: length × width × height = 170mm × 550mm × 120mm, with a total of 21 layers of fins, of which the number of layers on the hot side is 10 layers, and the number of layers on the cold side is 11 layers

Description of drawings

Figure 1: Installation diagram of a single-layer air-liquid skin heat exchanger

Figure 2: Schematic diagram of the structure of a single-layer air-liquid skin heat exchanger

1- Outer surface

2- Inner surface

3- Inlet conduit

4- Outlet conduit

5- Radial sealing end

6- Axial sealing end

7-Single-layer cooling fins

8- Fuselage connecting flange

9- Aircraft outer skin

10-inlet distribution main pipe

11-Inlet distribution branch pipe

12- Outlet branch pipe

13- Liquid collection tube

14-Single layer air-liquid skin heat exchanger

Detailed ways

The present invention will be further described in detail through specific embodiments below.

The present invention adopts the boundary layer heat dissipation technology integrated with the aircraft skin, and designs a single-layer air-liquid skin heat exchanger attached to the outer surface of the aircraft skin. The inside of the skin heat exchanger is a thermal fluid ( No. 65 coolant), the external use of the relative speed of the aircraft and the ambient air to cool the thermal fluid, cancel the traditional ram air intake air cooling method, due to the air-liquid skin heat exchanger (the internal flow is hot liquid) Compared with the air-air skin heat exchanger (hot air flows inside), it has higher heat exchange capacity and cooling effect, so the invention can minimize the fuel compensation loss of the aircraft.

Working process: The hot fluid (No. 65 coolant) coming out of the electronic equipment enters the "liquid inlet distribution main pipe 10" through the "liquid inlet pipe 3", and then enters the independent "single-layer liquid mask" from the "liquid inlet distribution branch pipe 11". Skin heat exchanger 14", the hot fluid in the liquid skin heat exchanger exchanges heat with the external ram air and cools down, then enters the "liquid outlet collection pipe 13" through the "liquid outlet branch pipe 12", and finally passes through the "outlet liquid collector pipe 13". The liquid conduit 4" flows out into the electronic equipment, and the electronic equipment is cooled again to ensure that the electronic equipment works in a suitable temperature range.

Taking a certain type of aircraft as an example, the thermal load of electronic equipment is 13kW, the flight time is 4h, and the aircraft is flying at cruising altitude. If an air-liquid skin heat exchanger is used instead of an air-liquid heat When the ram air volume is 2160kg/h, it can reduce the compensatory loss of aircraft fuel by 307kg, and extend the flight time by 10 minutes (the extended flight time includes the flight time increased by canceling the ram inlet drum to reduce the aerodynamic resistance of the aircraft). The external dimensions of the above-mentioned air-liquid heat exchanger are: length×width×height=170mm×550mm×120mm, wherein the number of layers on the hot side is 10 layers, and the number of layers on the cold side is 11 layers.

If the "single-layer air-liquid skin heat exchanger" is invented by using the technology of this scheme, under the same input conditions, the skin heat exchange area required by the system is 2.72m2, assuming that the diameter of the aircraft is 2m, the skin required at this time The area is equivalent to one 433mm ring.

Claims (5)

1. aircraft individual layer air-liquid covering heat change method, it is characterized in that, at the fuselage outside face individual layer air-liquid covering H Exch is installed, this air-liquid covering H Exch comprises outside face (1), inside face (2), feed liquor conduit (3), go out fluid catheter (4), sealing termination (5), (6), and with fuselage connecting bridge (8), installation individual layer radiating fin (7) between outside face (1) and inside face (2).

2. aircraft individual layer air according to claim 1-liquid covering heat change method, it is characterized in that, described air-liquid covering H Exch is attached at the fuselage skin outside face, and the fuselage skin outside face is with air-employing of liquid covering H Exch is spirally connected or the airtight mode of being spirally connected is connected.

3. aircraft individual layer air according to claim 1-liquid covering heat change method, it is characterized in that, described fuselage outside face is removed local covering, embeds air-liquid covering H Exch, and the fuselage outside face is with air-employing of liquid covering H Exch is spirally connected or the airtight mode of being spirally connected is connected.

4. aircraft individual layer air according to claim 1-liquid covering heat change method is characterized in that, described air-liquid covering H Exch material therefor is an aluminum alloy.

5. aircraft individual layer air according to claim 1-liquid covering heat change method is characterized in that, described outside face (2) is processed to form shallow table rib line by special process.

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