CN-122014367-A - Aircraft active cooling method and system based on heat sink cascade utilization

CN122014367ACN 122014367 ACN122014367 ACN 122014367ACN-122014367-A

Abstract

The invention provides an aircraft active cooling method based on heat sink cascade utilization, which at least comprises the steps of introducing a cooling medium into a liquid cooling channel of a generator controller, conducting heat exchange between the cooling medium and the generator controller, introducing the cooling medium subjected to primary heat absorption into an active cooling channel of a generator main body, conducting heat exchange between the cooling medium and the generator main body, atomizing the cooling medium subjected to secondary heat absorption into ram air leading to a power turbine when the temperature of the ram air exceeds the tolerance temperature of the power turbine, reducing the temperature of the ram air through the heat absorption of evaporation of the cooling medium, and selectively discharging outlet air subjected to expansion work of the power turbine into the atmosphere or introducing the outlet air into an aircraft bearing structure for active cooling. The invention further provides an aircraft active cooling system based on heat sink cascade utilization. The invention has the beneficial effects that the utilization efficiency of limited heat sink on the aircraft can be greatly improved.

Inventors

ZENG HONGGANG
CHEN LONG
LI KUN
DU CHENHUI
ZHU JIAWEI

Assignees

中国航空研究院

Dates

Publication Date: 20260512
Application Date: 20260206

Claims (10)

1. An aircraft active cooling method based on heat sink cascade utilization is characterized by comprising the following steps: Introducing a cooling medium into a liquid cooling channel of a generator controller, and performing heat exchange between the cooling medium and the generator controller to finish primary heat absorption; Introducing the cooling medium subjected to primary heat absorption into an active cooling flow channel of the generator main body, and performing heat exchange between the cooling medium and the generator main body to finish secondary heat absorption; Atomizing the cooling medium after reabsorbing heat into the ram air leading to the power turbine when the temperature of the ram air exceeds the tolerance temperature of the power turbine, reducing the temperature of the ram air by the absorption of heat by evaporation of the cooling medium; And selectively discharging the outlet air after the power turbine expands and does work into the atmosphere or leading the outlet air into a load-carrying structure of the aircraft for active cooling.
2. The heat sink cascade utilization-based aircraft active cooling method of claim 1, wherein temperature control of inlet air to the power turbine is achieved by adjusting a mass flow ratio of the cooling medium atomized into to the ram air to the power turbine.
3. The aircraft active cooling method based on heat sink cascade utilization according to claim 1, wherein the cooling medium is atomized into droplets of 5-30 μm through an atomizing nozzle under the action of medium tank pressure and/or liquid pump pressurization.
4. The heat sink cascade utilization-based aircraft active cooling method of claim 1, wherein the cooling medium after reabsorbing is recovered through a bypass circuit when the ram air temperature is below the power turbine withstand temperature.
5. The heat sink cascade utilization-based aircraft active cooling method of claim 1, wherein an outlet air flow direction of the power turbine is determined according to a flight condition parameter of the aircraft; The working condition parameters of the aircraft at least comprise the flying speed of the aircraft, the temperature of the load bearing structure of the aircraft and the power generation power of the power turbine.
6. The heat sink cascade utilization-based aircraft active cooling method of claim 1, wherein the temperature control of the cooling medium is coordinated with a thermal control system of the aircraft, and the temperature of the cooling medium is actively regulated by fuel oil or circulating cooling liquid to be maintained in a preset temperature range.
7. An aircraft active cooling system based on heat sink cascade utilization, characterized in that it is applied to an aircraft active cooling method based on heat sink cascade utilization according to any one of claims 1 to 6, comprising: a medium tank for storing a cooling medium; the liquid cooling channel is laid on the generator controller and is connected with the medium storage tank through a first pipeline; the active cooling flow passage is laid on the generator main body and is connected with the liquid cooling passage through a second pipeline; The atomization nozzle is arranged in the air taking channel in front of the inlet of the power turbine and is connected with the active cooling flow channel through a third pipeline.
8. The heat sink cascade utilization-based aircraft active cooling system of claim 7, further comprising a three-way valve having an inlet end in communication with the active cooling flow channel, a first outlet end in communication with the third conduit, and a second outlet end in communication with the media tank via a bypass circuit.
9. The heat sink cascade utilization-based aircraft active cooling system of claim 7, wherein a circulation cooling circuit is arranged outside the medium storage tank, and fuel oil or circulation cooling liquid circulates in the circulation cooling circuit.
10. The aircraft active cooling system based on heat sink cascade utilization of claim 7, wherein a flow control valve is arranged on the first pipeline, and temperature monitoring devices are arranged in the medium storage tank, the generator controller, the generator main body and the air intake channel.

Description

Aircraft active cooling method and system based on heat sink cascade utilization Technical Field The invention relates to the technical field of aircraft energy and thermal management, in particular to an aircraft active cooling method and system based on heat sink cascade utilization, which are particularly suitable for cooling a power turbine power generation system and a bearing structure. Background With the rapid development of aerospace technology, the flight speed of the aircraft is faster and faster, so that the ram air is severely compressed and the temperature is obviously increased, and the heated ram air is difficult to effectively thermally control the heating component when the aircraft flies at high speed. Namely, the advanced aircraft has extremely bad thermal environment caused by high flying speed, the traditional aircraft system and equipment thermal control and high-temperature bearing structure cooling method is difficult to use, and the advanced aircraft has more and more outstanding thermal safety problems. In order to reduce the performance compensation loss of the aircraft system and equipment thermal control and the structural active cooling system, on the basis of finely designing an anti-heat insulation scheme and comprehensively utilizing natural heat sinks such as structures, fuel oil and the like and consumable heat sinks of an aircraft carrier band and the like by combining the actual temperature region regulation and control requirements of thermal control objects, on-line heat sink generation and cascade utilization methods are explored so as to realize the maximization of effective heat sink utilization efficiency. For example, chinese patent publication No. CN118442141a discloses a high enthalpy ram air turbine power generation system thermal management scheme, the structure includes a turbine stator, a turbine rotor, a motor, a water tank and an oil tank, the turbine stator adopts a sweating cooling scheme, and the turbine rotor adopts a fuel cooling scheme. The turbine stator blade, the movable blade and the wheel disc are internally provided with cooling channels, and the water cooling stator blade, the fuel oil is used for cooling the movable blade and the wheel disc, so that the temperature of the turbine is reduced to be within a material allowable range, and the turbine works stably and safely. According to the invention, the air flow temperature entering the movable blade is further reduced by utilizing the capability of water evaporation and heat absorption while cooling the stationary blade, the flow of fuel oil required for cooling the movable blade and the wheel disc is reduced, clean ram air in a high-altitude environment is used, a better external environment is provided for sweating cooling, and the problem of cooling a hot end part of the existing high-enthalpy ram air turbine is solved. However, the stator and rotor of the turbine are cooled by both water and fuel, which requires a complex improved design of the air turbine, and the sweat cooling requires the introduction of a complex auxiliary system. The Chinese patent publication No. CN119102788A discloses a turbine power generation system for realizing high-enthalpy ram air cascade cooling, which comprises a first-stage heat exchanger, a second-stage heat exchanger, an oil-gas turbine, an air turbine and a split valve, wherein a hot-side inlet of the first-stage heat exchanger is connected with a high-temperature high-pressure air channel, a hot-side outlet of the first-stage heat exchanger is connected with a hot-side inlet of the second-stage heat exchanger, a hot-side outlet of the second-stage heat exchanger is connected with an inlet of the air turbine, an outlet of the air turbine is connected with an inlet of the split valve, an outlet of the split valve is connected with a cold-side inlet of the second-stage heat exchanger, an inlet of the oil-gas turbine is connected with a cracking oil-gas pipeline, and an outlet of the oil-gas turbine is connected with a cold-side inlet of the first-stage heat exchanger. The invention cools the high-temperature high-pressure air by sequentially utilizing the low-temperature pyrolysis gas after the expansion and cooling of the oil gas turbine and the low-temperature low-pressure air after the expansion and cooling of the air turbine, and the problem of complex system also exists. Accordingly, there is a need for an active cooling method and system for aircraft based on heat sink cascade utilization that addresses or mitigates the effects of the above problems from an overall perspective of the aircraft platform. Disclosure of Invention According to the aircraft active cooling method based on heat sink cascade utilization, the generator controller, the generator main body and the ram air are sequentially cooled through the cooling medium, and the ram air expands in the power turbine to generate power and low-temperature air for cooling the aircraft load beari