CN-121973942-A - Aircraft-engine integrated multistage adjustable thermal management system based on multiple heat sinks

CN121973942ACN 121973942 ACN121973942 ACN 121973942ACN-121973942-A

Abstract

The invention belongs to the technical field of aircraft thermal management, and particularly relates to an aircraft-engine integrated multistage adjustable thermal management system based on multiple heat sinks. A multi-stage adjustable thermal management network is constructed by integrating multiple heat sinks of fuel oil, air, coolant, phase change material and liquid hydrogen. The system dynamically switches the heat flow paths according to working conditions of low, medium and high Mach numbers, wherein fuel oil and air are used as main heat sinks at the low Mach number, a boosting fuel oil path is started to enhance cooling at the medium Mach number, a liquid hydrogen system is started at the high Mach number, the fuel oil is deeply cooled through a hydrogen-fuel heat exchanger, and heat load balance is realized by cooperation with a phase change heat storage device. The heat source and the heat sink are matched as required through the cooperative control of the multiple valves, so that the heat dissipation capacity and the adaptability of the system under the wide-envelope flight are obviously improved.

Inventors

GONG WEIJUN
LIN JUQIANG
XIE GANG

Assignees

天目山实验室

Dates

Publication Date: 20260505
Application Date: 20260228

Claims (10)

1. An aircraft-engine integrated multi-stage tunable thermal management system based on multiple heat sinks, comprising: An aircraft system and a phase change heat storage device arranged in heat exchange with the aircraft system; The system also comprises an engine system, wherein fuel oil stored in the aircraft system enters the engine system after the temperature of the fuel oil is adjusted by the phase-change heat storage device; the engine system comprises typical engine sub-components, an engine fuel system, a lubricating oil system and an engine air system; typical subcomponents of the engine include a main combustion chamber and an afterburner; The engine fuel system comprises a first oil way and a second oil way; when the fuel is in the first working condition, the fuel enters the main combustion chamber through the first oil way after the temperature of the fuel is regulated by the phase change heat storage device; When the phase change heat storage device is in a second working condition, fuel oil enters the main combustion chamber through the first oil way and enters the afterburner through the second oil way after the temperature of the fuel oil is regulated by the phase change heat storage device; The engine system further comprises a liquid hydrogen system, and the engine fuel system further comprises a third oil way; When the phase change heat storage device is in a third working condition, fuel oil enters the main combustion chamber through the first oil way after the temperature of the fuel oil is regulated by the phase change heat storage device, and enters the main combustion chamber after heat exchange with the liquid hydrogen system through the third oil way; The liquid hydrogen system enters the afterburner via a hydrogen fuel line.
2. The multi-heat sink based aircraft-engine integrated multi-stage tunable thermal management system of claim 1, wherein the aircraft system comprises an aircraft air system in heat exchange arrangement with the engine-typical sub-component that generates hot gas that is cooled by the aircraft air system and enters a cabin; the system also comprises a device cooling circulation system, a high-temperature coolant circulation system and an aircraft fuel system; the aircraft fuel system enables fuel to enter the phase change heat storage device; When the high-temperature coolant circulation system is in the first working condition and the second working condition, the high-temperature coolant circulation system exchanges heat with fuel oil of the aircraft fuel oil system; and when the high-temperature cooling agent is in the third working condition, the high-temperature cooling agent circulation system exchanges heat with the fuel oil of the aircraft fuel oil system after exchanging heat with the aircraft air system.
3. The multi-heat sink based aircraft-engine integrated multi-stage tunable thermal management system of claim 2, wherein the equipment cooling circulation system includes a low temperature coolant circulation system and an evaporation circulation system; The low-temperature coolant circulation system is in heat exchange arrangement with the electronic equipment with lower tolerance temperature, the low-temperature coolant circulation system transfers heat to the high-temperature coolant circulation system through the evaporation circulation system, and the high-temperature coolant circulation system is in heat exchange arrangement with the electronic equipment with higher tolerance temperature; The high-temperature coolant circulation system transfers heat of the electronic equipment to fuel oil when the electronic equipment is in the first working condition and the second working condition; And when the air conditioner is in the third working condition, the high-temperature coolant circulation system transfers the heat of the electronic equipment and the heat of the air system of the airplane to fuel oil.
4. The multi-heat sink based aircraft-engine integrated multi-stage tunable thermal management system of claim 3, wherein the first operating mode is selected for low mach number flight; Selecting the second working condition when the medium Mach number flies; and selecting the third working condition when the Mach number flies.
5. A multi-heat sink based aircraft-engine integrated multi-stage adjustable thermal management system according to claim 3, characterized in that a seventh two-position three-way valve (7) is provided in the high temperature coolant circulation system; When the working conditions are in the first working condition and the second working condition, working medium in the high-temperature coolant circulation system flows among a condenser of the evaporation circulation system, electronic equipment with higher tolerance temperature, the seventh two-position three-way valve (7) and a fuel/coolant heat exchanger of the aircraft fuel system; When the working medium is in the third working condition, working medium in the high-temperature coolant circulation system flows among a condenser of the evaporation circulation system, electronic equipment with higher tolerance temperature, the seventh two-position three-way valve (7), an air/coolant heat exchanger of the aircraft air system and a fuel/coolant heat exchanger of the aircraft fuel system.
6. The multi-heat sink based aircraft-engine integrated multi-stage adjustable thermal management system of claim 3, wherein the engine fuel system further comprises a servo oil circuit, and fuel enters the servo oil circuit after passing through the phase change heat storage device to provide servo fuel when in the first, second and third conditions.
7. The multi-heat sink based integrated multi-stage adjustable thermal management system of an aircraft-engine of claim 1, wherein the first oil circuit comprises a main fuel oil pump, a fuel oil heat exchanger, a seal production bleed air heat exchanger and a first two-position three-way valve (1) which are sequentially communicated; the oil inlet end of the main fuel oil pump is communicated with the oil outlet end of the phase change heat storage device; The oil inlet end of the first two-position three-way valve (1) is communicated with the oil outlet end of the seal production air-entraining heat exchanger; The first outlet of the first two-position three-way valve (1) is communicated with the main combustion chamber; when the first working condition and the second working condition are met, the second outlet of the first two-position three-way valve (1) is closed; The seal producing bleed air heat exchanger is arranged in heat exchange relationship with the hot air produced by the engine typical subcomponent.
8. The multi-heat sink based aircraft-engine integrated multi-stage adjustable thermal management system of claim 7, wherein the second oil circuit comprises a boost fuel pump in communication with an oil outlet end of the phase change heat storage device; The valve also comprises a second two-position three-way valve (2) and a fifth two-position three-way valve (5); the first oil inlet end of the second two-position three-way valve (2) and the first oil inlet end of the fifth two-position three-way valve (5) are communicated with the oil outlet end of the boost fuel pump; the second oil inlet end of the second two-position three-way valve (2) is communicated with the second outlet of the first two-position three-way valve (1), the outlet of the second two-position three-way valve (2) is communicated with the oil inlet end of the low-pressure bleed air heat exchanger, the oil outlet end of the low-pressure bleed air heat exchanger is communicated with the oil inlet end of a third two-position three-way valve (3), and the first oil outlet end of the third two-position three-way valve (3) is communicated with the afterburner; The oil outlet end of the fifth two-position three-way valve (5) is communicated with the oil inlet end of the high-pressure air-entraining heat exchanger, the oil outlet end of the high-pressure air-entraining heat exchanger is communicated with the oil inlet end of the sixth two-position three-way valve (6), the first oil outlet end of the sixth two-position three-way valve (6) is communicated with the main combustion chamber, and the second oil outlet end of the sixth two-position three-way valve (6) is communicated with the afterburner; the low-pressure bleed air heat exchanger and the high-pressure bleed air heat exchanger are arranged in heat exchange with hot air generated by typical sub-components of the engine; When the first working condition and the third working condition are met, the forced fuel oil pump is closed; When the engine is in the second working condition, the boost fuel oil pump is started, and fuel oil enters the afterburner through a first passage formed by the second two-position three-way valve (2), the low-pressure bleed air heat exchanger and the third two-position three-way valve (3), a second passage formed by the fifth two-position three-way valve (5), the high-pressure bleed air heat exchanger and the sixth two-position three-way valve (6) respectively.
9. The multi-heat sink based aircraft-engine integrated multi-stage adjustable thermal management system of claim 8, wherein the liquid hydrogen system comprises a hydrogen storage tank, a hydrogen pump and a hydrogen-burning heat exchanger which are arranged in communication; The air outlet end of the hydrogen combustion heat exchanger is communicated with the afterburner; The hydrogen-burning heat exchanger is in heat exchange arrangement with the third oil way; and when the third working condition is met, liquid hydrogen in the hydrogen storage tank enters the afterburner through the hydrogen pump and the hydrogen-combustion heat exchanger.
10. The multi-heat sink based aircraft-engine integrated multi-stage adjustable thermal management system of claim 9, wherein the third oil circuit comprises a fourth two-position three-way valve (4); the oil inlet end of the fourth two-position three-way valve (4) is communicated with the oil outlet end of the hydrogen-burning heat exchanger, and the oil inlet end of the hydrogen-burning heat exchanger is communicated with the second oil outlet end of the third two-position three-way valve (3); The first oil outlet end of the fourth two-position three-way valve (4) is communicated with the second oil inlet end of the fifth two-position three-way valve (5), and the second oil outlet end of the fourth two-position three-way valve (4) is communicated with the oil inlet end of the phase change heat storage device; When the low-pressure bleed air heat exchanger is in the third working condition, a first outlet of the first two-position three-way valve (1) is closed, fuel enters the second two-position three-way valve (2) through a second outlet of the first two-position three-way valve (1), and is split at the fourth two-position three-way valve (4) after passing through an oil way of the second two-position three-way valve (2), the low-pressure bleed air heat exchanger and the third two-position three-way valve (3); Wherein, part of fuel oil enters the main combustion chamber from the first oil outlet end of the fourth two-position three-way valve (4) through the fifth two-position three-way valve (5), the high-pressure air-entraining heat exchanger and the sixth two-position three-way valve (6); part of fuel oil enters the main combustion chamber from the second oil outlet end of the fourth two-position three-way valve (4) through the phase-change heat storage device and the first oil way.

Description

Aircraft-engine integrated multistage adjustable thermal management system based on multiple heat sinks Technical Field The invention belongs to the technical field of aircraft thermal management, and particularly relates to an aircraft-engine integrated multistage adjustable thermal management system based on multiple heat sinks. Background With the development of hypersonic aircrafts to higher Mach numbers and wider flight envelopes, the problems of pneumatic heating, structural heat transfer, heating of onboard high-power equipment and the like are increasingly severe, so that the overall heat load is rapidly increased, and the comprehensive performance of an aircraft thermal management system is challenged unprecedented. Currently, aircraft and engine thermal management system designs typically employ relatively independent architectures, the thermal management capabilities of which rely largely on single or limited heat sink resources. For example, fuel is the most commonly used primary heat sink due to its readily available and ultimately heat-rejecting nature through combustion. However, fuel itself has a limited specific heat capacity, with a definite upper limit on its temperature rise space and heat absorption capacity. With the increase of the flying speed, under the generated large-scale and continuous thermal load impact, the heat dissipation requirement of the system is difficult to meet only by relying on the fuel heat sink, and the heat dissipation requirement becomes a key bottleneck for restricting the improvement of the performance of the aircraft. Attempts to introduce multiple auxiliary heat sinks have been made in the prior art to break through the cooling capacity limitation of a single heat sink, however, these technical means often exhibit a "separate from the government" state, lacking integration and synergy at the system level. In different flight phases, the heat source distribution and the heat flux density of each area of the aircraft are characterized by high dynamic and time-varying properties. The existing architecture is difficult to carry out efficient overall allocation and dynamic allocation according to the working conditions which change in real time. The system cannot achieve maximization of heat sink utilization efficiency, an unbalanced situation that a high-efficiency heat sink is idle and a main heat sink is overwhelmed possibly occurs, and meanwhile, the buffer capacity of carrying out peak clipping and valley filling on transient high heat flow is also lacked, and the safety margin of system operation and the adaptability to complex working conditions are required to be improved. It can be seen that the defects of the prior art are mainly that the integrated design and intelligent cooperative mechanism is lack between the multi-heat sink resources, and the on-demand and dynamic matching of the heat load and the cooling capacity in the full flight envelope cannot be realized. The overall efficiency of the system is limited and the flexibility is insufficient. Accordingly, there is a need for an aircraft-engine integrated multi-stage tunable thermal management system based on multiple heat sinks to address the above-described issues. Disclosure of Invention It is an object of the present invention to provide an aircraft-engine integrated multi-stage tunable thermal management system based on multiple heat sinks to solve the above-mentioned problems. In order to achieve the above object, the present invention provides the following solutions: An aircraft-engine integrated multi-stage tunable thermal management system based on multiple heat sinks, comprising: An aircraft system and a phase change heat storage device arranged in heat exchange with the aircraft system; The system also comprises an engine system, wherein fuel oil stored in the aircraft system enters the engine system after the temperature of the fuel oil is adjusted by the phase-change heat storage device; the engine system comprises typical engine sub-components, an engine fuel system, a lubricating oil system and an engine air system; typical subcomponents of the engine include a main combustion chamber and an afterburner; The engine fuel system comprises a first oil way and a second oil way; when the fuel is in the first working condition, the fuel enters the main combustion chamber through the first oil way after the temperature of the fuel is regulated by the phase change heat storage device; When the phase change heat storage device is in a second working condition, fuel oil enters the main combustion chamber through the first oil way and enters the afterburner through the second oil way after the temperature of the fuel oil is regulated by the phase change heat storage device; The engine system further comprises a liquid hydrogen system, and the engine fuel system further comprises a third oil way; When the phase change heat storage device is in a third working condition, fuel oil enters the ma