CN215944913U - Heat exchange device for cooling aircraft fuel system - Google Patents
Heat exchange device for cooling aircraft fuel system Download PDFInfo
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- CN215944913U CN215944913U CN202122229771.6U CN202122229771U CN215944913U CN 215944913 U CN215944913 U CN 215944913U CN 202122229771 U CN202122229771 U CN 202122229771U CN 215944913 U CN215944913 U CN 215944913U
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Abstract
The invention provides a heat exchange device for cooling an aircraft fuel system, and belongs to the field of aircraft fuel systems. Comprises a cooling liquid outlet, a cooling liquid inlet, a fuel outlet, a baffle plate, a fuel channel and a cooling liquid channel. The cooling liquid outlet and the cooling liquid inlet are axially arranged at two ends of the outer surface of the heat exchange device in a split manner; the fuel oil channel is arranged in the heat exchange device and consists of straight pipelines which are arranged in parallel, and a fuel oil inlet and a fuel oil outlet are respectively arranged at two ends of each straight pipeline; the baffle plates are arranged at intervals up and down along the axial direction at equal intervals, and cooling liquid can be effectively mixed in a cooling liquid channel formed by the baffle plates. The cooling liquid outlet and the fuel oil inlet are positioned on the same side of the heat exchange device, and the cooling liquid inlet and the fuel oil outlet are positioned on the same side of the heat exchange device.
Description
Technical Field
The invention belongs to the field of aircraft fuel systems, and particularly relates to a cooling device for an aircraft fuel system.
Background
The heat exchange device related to cooling in the existing aircraft fuel system mainly comprises a fuel heat dissipation pump, a fuel-air heat exchanger, a fuel-liquid heat exchanger, a fuel-hydraulic oil heat exchanger, a fuel-lubricating oil heat exchanger and the like. The fuel-air heat exchanger and the fuel-liquid heat exchanger are generally tube fin type heat exchangers, and the fuel-hydraulic oil heat exchanger and the fuel-lubricating oil heat exchanger are generally shell-and-tube type heat exchangers. With the continuous development of aviation technology, the architecture of the aircraft fuel cooling system is gradually updated to meet the requirements of new aircraft. The problem that current aircraft fuel oil system exists is, the aircraft oil feeding system usually can carry out the hot oil return when the engine is little, and surplus fuel cools off and gets back to the fuel tank through the pipeline through ram air-fuel heat exchanger, and when the flight mach number of aircraft was higher, ram air temperature was also very high, is difficult to carry out abundant cooling to fuel, leads to getting back to the fuel temperature of fuel tank too high, and then has reduced the fuel heat accumulation ability, and the temperature can influence the oil tank security even if too high.
Disclosure of Invention
The invention provides a heat exchange device for cooling an aircraft fuel system, which is mainly used for cooling hot return oil under the condition of high flight Mach number of an aircraft and can also be expanded to other cooling parts of the aircraft.
Based on the purpose, the technical scheme adopted by the invention is as follows:
a heat exchange device for cooling an aircraft fuel system comprises a coolant outlet 1, a coolant inlet 2, a fuel inlet 3, a fuel outlet 4, a baffle 5, a fuel channel 6 and a coolant channel 7.
The cooling liquid outlet 1 and the cooling liquid inlet 2 are axially arranged at two ends of the outer surface of the heat exchange device in a split manner; the fuel oil channel 6 is arranged in the heat exchange device and consists of parallel straight pipelines, and a fuel oil inlet 3 and a fuel oil outlet 4 are respectively arranged at two ends of each straight pipeline; the baffle plates 5 are arranged at intervals up and down along the axial direction at equal intervals, and cooling liquid can be effectively mixed in a cooling liquid channel 7 formed by the baffle plates. The cooling liquid outlet 1 and the fuel oil inlet 3 are positioned on the same side of the heat exchange device, and the cooling liquid inlet 2 and the fuel oil outlet 4 are positioned on the same side of the heat exchange device.
Compared with the prior art, the invention has the following beneficial effects:
1, when the airplane flies at a high Mach number, the invention can utilize the cooling liquid to cool the hot return oil, thereby solving the problem that the hot return oil cannot be cooled due to overhigh temperature of the ram air;
the invention arranges the fuel oil flow channel in the straight channel and the cooling liquid in the bent channel formed by the baffle plate, so the pressure drop of the fuel oil side is relatively small.
Drawings
FIG. 1 is a schematic illustration of an apparatus for aircraft fuel system cooling according to the present invention;
FIG. 2 is a schematic diagram of the configuration of the device for aircraft fuel system cooling of the present invention;
FIG. 3 is a schematic view of the baffle structure of the cooling device of the present invention;
in the figure, 1 coolant outlet, 2 coolant inlet, 3 fuel inlet, 4 fuel outlet, 5 baffle, 6 fuel channel, 7 coolant channel.
Detailed Description
The invention is further described with reference to the following examples and figures:
example 1
As shown in fig. 1-2, a heat exchange device for cooling an aircraft fuel system comprises a coolant outlet 1, a coolant inlet 2, a fuel inlet 3, a fuel outlet 4, a baffle 5, a fuel passage 6 and a coolant passage 7.
As shown in fig. 2, the fuel inlet 3 is a hot return oil inlet behind a fuel supply main pipe of an aircraft fuel system, the coolant inlet 2 is a liquid water inlet, fuel exchanges heat with liquid water outside a fuel channel 6 to transfer heat to the liquid water, the cooled fuel flows out from the fuel outlet 4, and the liquid water absorbing heat flows out from the coolant outlet 1.
As shown in fig. 3, a baffle plate is arranged between the fuel passage 6 and the coolant passage 7, and the fuel flows in the fuel passage 6 in the direction opposite to the direction of the liquid water in the coolant passage 7, so that heat exchange can be better realized.
Example 2
The difference between this embodiment and embodiment 1 is that in this embodiment, the coolant is aviation 65 # coolant. The concrete structure is as follows:
as shown in fig. 1-2, a heat exchange device for cooling an aircraft fuel system comprises a coolant outlet 1, a coolant inlet 2, a fuel inlet 3, a fuel outlet 4, a baffle 5, a fuel passage 6 and a coolant passage 7.
The fuel entry 3 is the hot oil return entry behind the aircraft fuel system fuel supply main pipe, and coolant liquid entry 2 is the cooling liquid entry of aviation No. 65, and the fuel carries out the heat transfer through fuel oil passageway 6 and the aviation No. 65 cooling liquid in the passageway outside, gives 65 cooling liquid with heat transfer, and the fuel after the cooling is flowed out by fuel outlet 4, and the No. 65 cooling liquid after the absorption heat is flowed out by cooling liquid export 1.
Finally, the description is as follows: the above embodiments are only used for illustrating the present invention and do not limit the technical solutions described in the present invention; although the present invention has been described in detail, those skilled in the art can make modifications or substitutions to the present invention; all such modifications and variations are intended to be included herein within the scope of this disclosure and the present invention and protected by the following claims.
Claims (1)
1. A heat exchange device for cooling an aircraft fuel system is characterized by comprising a coolant outlet (1), a coolant inlet (2), a fuel inlet (3), a fuel outlet (4), a baffle plate (5), a fuel channel (6) and a coolant channel (7);
the cooling liquid outlet (1) and the cooling liquid inlet (2) are axially arranged at two ends of the outer surface of the heat exchange device in a split manner; the fuel oil channel (6) is arranged in the heat exchange device and consists of parallel straight pipelines, and a fuel oil inlet (3) and a fuel oil outlet (4) are respectively arranged at two ends of each straight pipeline; the baffle plates (5) are arranged at intervals up and down along the axial direction at equal intervals, and cooling liquid can be mixed in a cooling liquid channel (7) formed by the baffle plates; the cooling liquid outlet (1) and the fuel inlet (3) are positioned on the same side of the heat exchange device, and the cooling liquid inlet (2) and the fuel outlet (4) are positioned on the same side of the heat exchange device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122229771.6U CN215944913U (en) | 2021-09-15 | 2021-09-15 | Heat exchange device for cooling aircraft fuel system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122229771.6U CN215944913U (en) | 2021-09-15 | 2021-09-15 | Heat exchange device for cooling aircraft fuel system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215944913U true CN215944913U (en) | 2022-03-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122229771.6U Active CN215944913U (en) | 2021-09-15 | 2021-09-15 | Heat exchange device for cooling aircraft fuel system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215944913U (en) |
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2021
- 2021-09-15 CN CN202122229771.6U patent/CN215944913U/en active Active
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