Airplane comprehensive thermal management adjusting system

Abstract

The invention discloses an airplane comprehensive heat management adjusting system. The system comprises an oil delivery tank, a first valve, an oil supply tank, a second valve, a first three-way valve, a third three-way valve, a fourth three-way valve, a fifth three-way valve, a second three-way valve and an engine which are sequentially connected through an oil pipeline, a fuel oil-air heat exchanger and a fuel oil-lubricating oil heat exchanger are sequentially connected between the third three-way valve and the fifth three-way valve through oil way pipelines. A fuel oil-hydraulic heat exchanger and an air-fuel oil heat exchanger are further sequentially connected between the fourth three-way valve and the oil supply tank through an oil way pipeline, a four-way valve is further arrangedon the oil way pipeline between the air-fuel oil heat exchanger and the oil supply tank, and the four-way valve is further communicated with the first three-way valve and the second three-way valve through an oil way pipeline. Airborne fuel oil and external ram air are reasonably utilized, and energy is saved; the fuel flow is reasonably distributed by adjusting the opening degree of the electromagnetic valve, the fuel quantity required by the aircraft engine is guaranteed, the purpose of heat dissipation is achieved, the temperature of an inlet of the engine is prevented from being too high,and the service life of the aircraft engine is prolonged.

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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