CN-121990168-A - Aviation hybrid engine with electric drive unit thermal management system

CN121990168ACN 121990168 ACN121990168 ACN 121990168ACN-121990168-A

Abstract

The invention provides an aviation hybrid engine with an electric drive unit thermal management system, which comprises an aircraft fuel tank, an air fuel radiator and an electric drive unit thermal management system, wherein the electric drive unit thermal management system is independent of a fuel flow path of the aviation hybrid engine, and is connected in series between the air fuel radiator and the aircraft fuel tank, and cooling fuel is continuously provided for an electric drive unit through the electric drive unit thermal management system. The invention can ensure that cooling medium with proper flow pressure and lower temperature is provided for the propulsion motor stator and the propulsion motor controller, thereby meeting the temperature and pressure requirements of the propulsion motor stator and the propulsion motor controller, absorbing the heat generation of the propulsion motor stator and the propulsion motor controller, ensuring the normal operation of the propulsion motor and the motor controller and improving the safety of the aviation hybrid power engine.

Inventors

LIU RUJIA
LIN ZHIHUI
CHEN XIAO
Lv Lulu

Assignees

中国航发商用航空发动机有限责任公司

Dates

Publication Date: 20260508
Application Date: 20241106

Claims (10)

1. The aviation hybrid engine with the electric drive unit thermal management system is characterized by comprising an aircraft fuel tank, an air fuel radiator and an electric drive unit thermal management system, wherein the electric drive unit thermal management system is independent of a fuel flow path of the aviation hybrid engine, and is connected in series between the air fuel radiator and the aircraft fuel tank, and cooling fuel is continuously provided for an electric drive unit through the electric drive unit thermal management system.
2. The aircraft hybrid engine with electric drive unit thermal management system of claim 1, wherein the electric drive unit thermal management system includes an electric oil pump, a propulsion motor controller coolant flow passage, and a propulsion motor stator coolant flow passage in series, the electric oil pump being connected to the aircraft fuel tank, the propulsion motor stator coolant flow passage being connected to the air-fuel radiator.
3. An aircraft hybrid engine with electric drive unit thermal management system according to claim 2, wherein a fuel filter is connected between the air fuel radiator and the aircraft fuel tank.
4. The aircraft hybrid engine with electric drive unit thermal management system of claim 2, wherein the fuel outlet of the aircraft fuel tank is connected to the fuel inlet of the electric oil pump by a fluid line.
5. The aircraft hybrid engine with electric drive unit thermal management system of claim 4, wherein the fuel outlet of the electric oil pump is connected to the fuel inlet of the propulsion motor controller cooling medium flow passage by a fluid line.
6. The aircraft hybrid engine with electric drive unit thermal management system of claim 5, wherein the fuel outlet of the propulsion motor controller cooling medium flow passage is connected to the fuel inlet of the propulsion motor stator cooling medium flow passage by a fluid line.
7. The aircraft hybrid engine with electric drive unit thermal management system of claim 6, wherein a fuel outlet of the propulsion motor stator coolant flow passage is connected to a fuel inlet of the air-fuel radiator by a fluid line.
8. The aircraft hybrid engine with electric drive unit thermal management system of claim 7, wherein the fuel outlet of the air fuel radiator is connected to the fuel inlet of the fuel filter by a fluid line, the fuel outlet of the fuel filter is connected to the fuel inlet of the aircraft fuel tank, and the cooled fuel is returned to the aircraft fuel tank.
9. The aircraft hybrid engine with electric drive unit thermal management system of claim 1, further comprising an open rotor fan, a propulsion motor, a prime mover compressor, and an engine turbine, wherein the open rotor fan, the propulsion motor, an inlet portion of the prime mover compressor, and a low pressure turbine portion of the engine turbine are coaxially connected.
10. The aircraft hybrid engine with an electric drive unit thermal management system of claim 9, further comprising a prime mover compressor, a prime mover turbine, a prime mover nacelle cover, and a propulsion motor controller, the high pressure compressor portion of the prime mover compressor and the high pressure turbine portion of the prime mover turbine being coaxially connected; The air-fuel radiator and the propulsion motor controller are located between the nacelle cover and the engine turbine.

Description

Aviation hybrid engine with electric drive unit thermal management system Technical Field The invention relates to an aviation hybrid power engine thermal management system, in particular to an aviation hybrid power engine with an electric drive unit thermal management system. Background Under the guidance of targets such as carbon neutralization and green aviation, the aviation industry is faced with increasingly stringent emissions and economic requirements. Therefore, the hybrid power technology demand of new energy sources with new configurations is focused, and the aviation hybrid power engine is developed. An electric drive unit in a hybrid powertrain includes a propulsion motor and a propulsion motor controller. The propulsion motor and propulsion motor controller may generate higher heat due to the higher power of the electric drive unit. While the propulsion motor typically allows an operating temperature of no more than 200 ℃, the propulsion motor controller typically does not allow an operating temperature of more than 100 ℃. Therefore, it is necessary to use a cooling medium to dissipate heat from the propulsion motor and the propulsion motor controller and to implement a thermal management system architecture design. Since most of the heat of the propulsion motor is generated by the motor stator, the thermal management system of the propulsion motor currently in common use is to immerse the motor stator in an insulating cooling medium. The propulsion motor controller is provided with a cooling medium flow passage, and the cooling medium takes away the heat of the propulsion motor controller when flowing through the cooling medium flow passage. The current thermal management of the aviation hybrid engine for the electric drive unit mainly has the following problems: 1. The propulsion motor of the aviation hybrid power engine has higher power which can reach more than megawatt level, and the high-power propulsion motor can generate larger heat when working, so that the temperature of the propulsion motor is rapidly increased. Too high temperature of the propulsion motor can lead to coking of a cooling medium of the propulsion motor, and simultaneously, the permanent magnet of the propulsion motor can be demagnetized, so that the safety and the service life of the propulsion motor are affected. The heat generated by the propulsion motor controller is larger when the propulsion motor controller works, and part of the components are sensitive to temperature, so that the requirement on the temperature of the cooling medium is higher. 2. Lubricating oil and fuel oil are cooling mediums commonly used in aircraft engines. In the engine fuel oil flow path and the lubricating oil flow path, lubricating and cooling of bearings, seals, splines and gears are realized by the lubricating oil through the oil supply subsystem, the oil return subsystem and the ventilation subsystem, and the cyclic utilization of the lubricating oil in the engine is ensured. After the fuel oil is supplied to the engine by the aircraft, the fuel oil is pressurized by the fuel pump, then the functions of supplying the fuel oil to the combustion chamber, actuating the servo device and the like are realized through the fuel oil metering device and the fuel oil distribution device, and heat exchange is carried out between the fuel oil and the lubricating oil through the fuel oil heat exchanger. However, when the fuel and the oil in the motor fuel flow path and the oil flow path are used as a cooling medium, there are the following problems when the present invention is applied to an electric drive unit thermal management system: And the lubricating oil is adopted as a cooling medium, so that an additional lubricating oil tank is needed, the whole weight of the engine is increased, and the economical efficiency is reduced. In addition, under partial high-temperature working conditions, the oil supply temperature of the lubricating oil is higher, the heat transfer capacity of the lubricating oil radiator is limited, the lubricating oil is difficult to cool to the limiting temperature of the cooling medium inlet of the propulsion motor controller, and the heat dissipation requirement of the propulsion motor controller cannot be met. By adopting the prime motor fuel as the cooling medium, the fuel pressure of the fuel pump after pressurization is higher, the compression resistance requirements of the propulsion motor and the propulsion motor controller are difficult to meet, the risk of leakage of the cooling medium in the electric drive unit is increased, and the safety of the electric drive unit is influenced. 3. In an aero-hybrid engine, the operating conditions of the prime mover and the propulsion motor are not perfectly matched. If the fuel oil system of the prime mover is used for cooling the electric drive unit, in some working conditions, the flow rates in the oil flow path and the fuel oil flow path in the prime mover are smaller