CN215944912U - Aircraft fuel cooling system - Google Patents
Aircraft fuel cooling system Download PDFInfo
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- CN215944912U CN215944912U CN202122229702.5U CN202122229702U CN215944912U CN 215944912 U CN215944912 U CN 215944912U CN 202122229702 U CN202122229702 U CN 202122229702U CN 215944912 U CN215944912 U CN 215944912U
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Abstract
An aircraft fuel cooling system belongs to the field of aircraft fuel systems. The system comprises a fuel consumption cabin, a fuel supply pump, a fuel heat dissipation pump, a one-way valve, a fuel-air heat exchanger, a fuel-liquid heat exchanger, a fuel-hydraulic oil heat exchanger, a fuel-generator lubricating oil heat exchanger, a turbine engine booster pump, a fuel-engine lubricating oil heat exchanger, a bypass valve, a water-fuel oil heat exchanger and a regulating valve. The framework can realize high-efficiency matching between the heat load of an aircraft environmental control system, a liquid cooling system, a hydraulic system and a lubricating oil system and the heat sink capacity of fuel oil, and improves the utilization rate of the heat sink of the fuel oil.
Description
Technical Field
The invention belongs to the field of aircraft fuel systems, and particularly relates to an aircraft fuel cooling system.
Background
The existing aircraft fuel system mainly comprises an oil supply system, an oil delivery control system, a ventilation pressurization system, an oil filling system, an oil drainage system, a cooling system and the like. By arranging a plurality of oil tanks at different positions (including wings) of the airplane, the gravity center of the airplane can be adjusted by controlling the oil supply and delivery sequence according to the flight condition, and good flight performance is realized. Meanwhile, fuel on the airplane is used as a large amount of usable heat sinks, heat of a plurality of heating parts of the airplane can be taken away through the fuel cooling system, and the heat finally enters the engine for combustion. One of the problems of the existing aircraft fuel cooling system is that fuel enters an environmental control system, a hydraulic system, a lubricating oil system and other parts to take away heat after being pressurized by a fuel heat radiating pump through a fuel supply main pipe in a consumption cabin, and heat exchange parts are a fuel-air heat exchanger, a fuel-hydraulic oil heat exchanger and a fuel-lubricating oil heat exchanger in sequence, but the cooling sequence of each system is not fixed at present. The second problem is that with the development of aviation technology, the power of the electronic equipment on board the aircraft is gradually increased, and the method of cooling the electronic equipment by forced convection of air is difficult to realize effective cooling, and a new high-efficiency cooling technology must be adopted.
Disclosure of Invention
Aiming at the problems of the existing aircraft fuel cooling system, the invention provides an aircraft fuel cooling system framework which can realize high-efficiency matching between the heat load of an aircraft environmental control system, a liquid cooling system, a hydraulic system and a lubricating oil system and the heat sink capacity of fuel, and improve the utilization rate of the heat sink of fuel.
Based on the purpose, the technical scheme adopted by the invention is as follows:
an aircraft fuel cooling system comprises a fuel consumption cabin 1, a fuel supply pump 2, a fuel heat dissipation pump 3, a one-way valve 4, a fuel-air heat exchanger 5, a fuel-liquid heat exchanger 6, a fuel-hydraulic oil heat exchanger 7, a fuel-generator lubricating oil heat exchanger 8, a turbine engine booster pump 9, a fuel-engine lubricating oil heat exchanger 10, a bypass valve 11, a water-fuel oil heat exchanger 12 and a regulating valve 13.
An oil supply pump 2 in the fuel consumption cabin 1 is respectively connected with a fuel heat radiation pump 3 and a turbine engine booster pump 9, the fuel heat radiation pump 3 is respectively connected with a fuel-air heat exchanger 5 and a fuel-liquid heat exchanger 6, and outlet pipelines of the fuel-air heat exchanger 5 and the fuel-liquid heat exchanger 6 are converged and then sequentially connected with a fuel-hydraulic oil heat exchanger group and a fuel-generator lubricating oil heat exchanger group; the fuel-hydraulic oil heat exchanger group is formed by connecting fuel-hydraulic oil heat exchangers 7 in parallel, and the fuel-generator lubricating oil heat exchanger group is formed by connecting fuel-generator lubricating oil heat exchangers 8 in parallel; an outlet pipeline of the fuel-generator lubricating oil heat exchanger group is connected with a turbine engine booster pump 9; an outlet pipeline of a turbine engine booster pump 9 is connected with a fuel-engine lubricating oil heat exchanger 10, and the fuel-engine lubricating oil heat exchanger 10 is communicated with a combustion chamber; the outlet pipeline of the fuel-generator lubricating oil heat exchanger 8 is also connected with a bypass valve 11, a water-fuel oil heat exchanger 12 and a regulating valve 13 in sequence, and finally returns to the fuel consumption cabin 1.
Further, the oil supply pump 2 is a hydraulic turbine pump, and the fuel oil heat dissipation pump 3 is an alternating current electric pump.
Further, the fuel-air heat exchanger 5, the fuel-hydraulic oil heat exchanger 7, the fuel-generator lubricating oil heat exchanger 8, the fuel-engine lubricating oil heat exchanger 10 and the water-fuel oil heat exchanger 12 are shell-and-tube heat exchangers.
Further, the fuel-liquid heat exchanger 6 is a tube fin heat exchanger.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the heat load distribution rule and the fuel oil heat sink characteristics of the environment-friendly system, the liquid cooling system, the hydraulic system, the lubricating oil system and other systems, the cascade utilization of the fuel oil heat sink is realized;
(2) the invention can solve the problem of heat load radiation of the electronic equipment which is increasing day by day, and the fuel-liquid heat exchanger is adopted to carry out forced convection cooling on the high-power electronic equipment;
(3) the invention can solve the problem of cooling hot return oil of the airplane under the condition of high flight Mach number, and the problem that the hot return oil is difficult to cool by high-temperature ram air is solved by cooling the high-temperature hot return oil by using liquid water.
Drawings
FIG. 1 is an aircraft fuel cooling system architecture diagram of the present invention;
FIG. 2 is a schematic diagram of the aircraft fuel cooling system components of the present invention;
in the figure, 1 fuel consumption cabin, 2 fuel supply pump, 3 heat dissipation pump, 4 one-way valve, 5 fuel-air heat exchanger, 6 fuel-liquid heat exchanger, 7 fuel-hydraulic oil heat exchanger, 8 fuel-generator lubricating oil heat exchanger, 9 turbine engine booster pump, 10 fuel-engine lubricating oil heat exchanger, 11 bypass valve, 12 water-fuel oil heat exchanger, 13 regulating valve.
Detailed Description
The invention is further described with reference to the following examples and figures:
example 1
As shown in fig. 1-2, an aircraft fuel cooling system comprises a fuel consuming cabin 1, a fuel supply pump 2, a fuel heat dissipation pump 3, a check valve 4, a fuel-air heat exchanger 5, a fuel-liquid heat exchanger 6, a fuel-hydraulic oil heat exchanger 7, a fuel-generator lubricating oil heat exchanger 8, a turbine engine booster pump 9, a fuel-engine lubricating oil heat exchanger 10, a bypass valve 11, a water-fuel oil heat exchanger 12 and a regulating valve 13.
As shown in fig. 2, the cooling fuel in the fuel cooling system flows from a fuel supply main pipe, and a part of the cooling fuel passes through a turbo engine booster pump 9 after passing through a fuel supply pump 2 of the engine; the other part of the oil passes through a fuel oil heat dissipation pump 3 and then is divided into two paths, wherein one path of the oil passes through a fuel oil-air heat exchanger 5 to cool air used by the environmental control system, the other path of the oil passes through a fuel oil-liquid heat exchanger 6 to take away heat absorbed by liquid used for cooling electronic equipment, then two paths of fuel oil are collected and respectively pass through a fuel oil-hydraulic oil heat exchanger 7 and a fuel oil-generator lubricating oil heat exchanger 8 to take away heat of a hydraulic system and a generator lubricating oil system, then the two paths of fuel oil enter a turbine engine booster pump 9, then a turbine engine main fuel oil regulator supplies the engine, the engine lubricating oil is cooled through the fuel oil-engine lubricating oil heat exchanger 10, and finally the engine lubricating oil is combusted and discharged by a combustion chamber. When the airplane is in an afterburning state, part of fuel oil is sent into an afterburner for combustion through an afterburning pump of a turbine engine. When the engine is in a small state, the bypass valve 11 is opened, and redundant fuel oil passes through the bypass valve, is cooled by the water-fuel heat exchanger 12 and then returns to the fuel oil consumption cabin 1.
Example 2
The difference between the embodiment and the embodiment 1 is that the cooling medium adopted by the water-fuel heat exchanger 12 in the embodiment is replaced by aviation 65 cooling liquid from liquid water. The concrete structure is as follows:
as shown in fig. 1-2, an aircraft fuel cooling system comprises a fuel consuming cabin 1, a fuel supply pump 2, a fuel heat dissipation pump 3, a check valve 4, a fuel-air heat exchanger 5, a fuel-liquid heat exchanger 6, a fuel-hydraulic oil heat exchanger 7, a fuel-generator lubricating oil heat exchanger 8, a turbine engine booster pump 9, a fuel-engine lubricating oil heat exchanger 10, a bypass valve 11, a water-fuel oil heat exchanger 12 and a regulating valve 13.
As shown in fig. 2, the cooling fuel in the fuel cooling system flows from a fuel supply main pipe, and a part of the cooling fuel passes through a turbo engine booster pump 9 after passing through a fuel supply pump 2 of the engine; the other part of the oil passes through a fuel oil heat dissipation pump 3 and then is divided into two paths, wherein one path of the oil passes through a fuel oil-air heat exchanger 5 to cool air used by the environmental control system, the other path of the oil passes through a fuel oil-liquid heat exchanger 6 to take away heat absorbed by liquid used for cooling electronic equipment, then two paths of fuel oil are collected and respectively pass through a fuel oil-hydraulic oil heat exchanger 7 and a fuel oil-generator lubricating oil heat exchanger 8 to take away heat of a hydraulic system and a generator lubricating oil system, then the two paths of fuel oil enter a turbine engine booster pump 9, then a turbine engine main fuel oil regulator supplies the engine, the engine lubricating oil is cooled through the fuel oil-engine lubricating oil heat exchanger 10, and finally the engine lubricating oil is combusted and discharged by a combustion chamber. When the airplane is in an afterburning state, part of fuel oil is sent into an afterburner for combustion through an afterburning pump of a turbine engine. When the engine is in a small state, the bypass valve 11 is opened, and redundant fuel oil passes through the bypass valve and returns to the fuel oil consumption cabin 1 after being cooled by aviation No. 65 coolant in the water-fuel oil heat exchanger 12.
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 (4)
1. An aircraft fuel cooling system is characterized by comprising a fuel consumption cabin (1), a fuel supply pump (2), a fuel heat dissipation pump (3), a one-way valve (4), a fuel-air heat exchanger (5), a fuel-liquid heat exchanger (6), a fuel-hydraulic oil heat exchanger (7), a fuel-generator lubricating oil heat exchanger (8), a turbine engine booster pump (9), a fuel-engine lubricating oil heat exchanger (10), a bypass valve (11), a water-fuel oil heat exchanger (12) and a regulating valve (13);
an oil supply pump (2) in the fuel consumption cabin (1) is respectively connected with a fuel heat dissipation pump (3) and a turbine engine booster pump (9), the fuel heat dissipation pump (3) is respectively connected with a fuel-air heat exchanger (5) and a fuel-liquid heat exchanger (6), and outlet pipelines of the fuel-air heat exchanger (5) and the fuel-liquid heat exchanger (6) are converged and then sequentially connected with a fuel-hydraulic oil heat exchanger group and a fuel-generator lubricating oil heat exchanger group; the fuel-hydraulic oil heat exchanger group is formed by connecting fuel-hydraulic oil heat exchangers (7) in parallel, and the fuel-generator lubricating oil heat exchanger group is formed by connecting fuel-generator lubricating oil heat exchangers (8) in parallel; an outlet pipeline of the fuel-generator lubricating oil heat exchanger group is connected with a turbine engine booster pump (9); an outlet pipeline of a turbine engine booster pump (9) is connected with a fuel-engine lubricating oil heat exchanger (10), and the fuel-engine lubricating oil heat exchanger (10) is communicated with a combustion chamber; the outlet pipeline of the fuel-generator lubricating oil heat exchanger (8) is also sequentially connected with a bypass valve (11), a water-fuel oil heat exchanger (12) and a regulating valve (13) and finally returns to the fuel consumption cabin (1).
2. An aircraft fuel cooling system according to claim 1, characterised in that the supply pump (2) is a hydraulic turbine pump and the fuel pump (3) is an electric ac motor pump.
3. An aircraft fuel cooling system according to claim 1, characterised in that the fuel-air heat exchanger (5), the fuel-hydraulic oil heat exchanger (7), the fuel-generator lubricating oil heat exchanger (8), the fuel-engine lubricating oil heat exchanger (10) and the water-fuel oil heat exchanger (12) are shell and tube heat exchangers.
4. An aircraft fuel cooling system according to claim 1, characterised in that the fuel-liquid heat exchanger (6) is a tube and fin heat exchanger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122229702.5U CN215944912U (en) | 2021-09-15 | 2021-09-15 | Aircraft fuel cooling system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122229702.5U CN215944912U (en) | 2021-09-15 | 2021-09-15 | Aircraft fuel cooling system |
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| CN215944912U true CN215944912U (en) | 2022-03-04 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20210172375A1 (en) * | 2019-12-09 | 2021-06-10 | Meggitt Aerospace Limited | Engine thermal management methods and control systems |
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- 2021-09-15 CN CN202122229702.5U patent/CN215944912U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20210172375A1 (en) * | 2019-12-09 | 2021-06-10 | Meggitt Aerospace Limited | Engine thermal management methods and control systems |
| US11492969B2 (en) * | 2019-12-09 | 2022-11-08 | Meggitt Aerospace Limited | Engine thermal management methods and control systems |
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