An aircraft integrated thermal management adjustment system

Abstract

The invention discloses an aircraft comprehensive thermal management adjustment system, which comprises a fuel delivery tank, a first valve, a fuel supply tank, a second valve, a first three-way valve, a third three-way valve, a forty-three The through valve, the fifth three-way valve, the second three-way valve and the engine, the third three-way valve and the fifth three-way valve are sequentially connected with a fuel-air heat exchanger and a fuel-lubricating oil heat exchanger through the oil pipeline A fuel-hydraulic heat exchanger and an air-fuel heat exchanger are sequentially connected between the fourth three-way valve and the fuel supply tank through an oil pipeline, and the oil pipeline between the air-fuel heat exchanger and the fuel supply tank A four-way valve is also provided, and the four-way valve is also connected to the first three-way valve and the second three-way valve through the oil pipeline; the present invention rationally utilizes the on-board fuel oil and external ram air to save energy; , Reasonable distribution of fuel flow not only ensures the amount of fuel required by the aircraft engine, but also achieves the purpose of heat dissipation, and avoids excessive engine inlet temperature, prolonging the life of the aircraft engine.

Description

technical field [0001] The invention belongs to the technical field of aviation thermal management, in particular to an aircraft comprehensive thermal management adjustment system. Background technique [0002] With the improvement of the overall performance of the aircraft, the number and power of on-board electronic equipment continue to increase, and the heat generated by the system naturally increases accordingly. In addition, in order to meet the stealth requirements of the aircraft, the number and area of ​​stamping openings on the exterior of the fuselage are limited, and the amount of ram air that can be used is limited. Moreover, ram bleed air is used to dissipate heat from the aircraft's on-board system. This method requires openings on the outer surface of the aircraft, which destroys the integrity of the aircraft's shape. At the same time, the ram bleed air cooling consumes the effective power of the aircraft engine and reduces the performance of the aircraft. ...

AI Technical Summary

Problems solved by technology

[0003] However, due to the increase of heat generated by various systems of the aircraft, the corresponding heat dissipation power of the heat exchanger also increases. Therefore, using fuel oil as a heat sink to dissipate heat from the aircraft system may cause the fuel temperature to exceed the required temperature at the engine inlet, causing engine failure to absorb heat. After the fuel is returned to the fuel supply tank, the temperature of the fuel in the fuel supply tank will increase, which may reach or exceed the inlet temperature limit of the engine

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