CN-121973941-A - Range-extending power generation system for aircraft and aircraft

CN121973941ACN 121973941 ACN121973941 ACN 121973941ACN-121973941-A

Abstract

The invention provides an extended range power generation system for an aircraft and the aircraft. The generator component comprises a first transmission shaft, and the oil pump component comprises a second transmission shaft and an oil duct provided with an oil inlet and an oil outlet. The first transmission shaft and the second transmission shaft are coaxially arranged and fixedly connected through interference fit. The first transmission shaft drives the second transmission shaft to synchronously rotate, and cooling liquid is sucked through the oil inlet and conveyed to the heat exchanger through the oil outlet so as to dissipate heat. The design eliminates independent driving and transmission parts, greatly simplifies the structure and realizes light weight. The interference fit transmission is stable, and the gap impact and aging fracture defects are eliminated. The coaxial drive ensures the synchronous circulation of the cooling liquid and precisely covers the heating component, avoids the risk of heat dissipation hysteresis in the starting stage, and ensures the operation stability of the range extender under the high-load working condition.

Inventors

ZHANG XINHAO
LIU YUCHENG
ZHANG DI
LEI ZHENGYU
ZHONG CHENG

Assignees

轾驱新能源(柳州)有限公司
河北科技大学

Dates

Publication Date: 20260505
Application Date: 20260129

Claims (10)

1. An extended range power generation system for an aircraft, the extended range power generation system comprising a generator assembly and an oil pump assembly integrated to one side of the generator assembly in a first direction; the oil pump assembly comprises a second transmission shaft and an oil duct, wherein the oil duct comprises an oil inlet and an oil outlet, the oil inlet is connected with the generator assembly, and the oil outlet is connected with the heat exchanger; the first transmission shaft and the second transmission shaft are coaxially arranged, and the first transmission shaft and the second transmission shaft are fixedly connected through interference fit, so that when the first transmission shaft rotates, the second transmission shaft is driven to synchronously rotate, and cooling liquid is sucked from the oil inlet and conveyed to the heat exchanger through the oil outlet for heat dissipation.
2. The extended range power generation system for an aircraft according to claim 1, wherein an end of the first drive shaft is provided with a mating hole, and an end of the second drive shaft is pressed into the mating hole to form the interference fit fixed connection.
3. The extended range power generation system for an aircraft of claim 1, wherein the first drive shaft and the second drive shaft have an interference fit tolerance in the range of 0.02mm to 0.05mm.
4. The extended range power generation system for an aircraft according to claim 1, wherein the surface roughness Ra of the mating end surfaces of the first drive shaft and the second drive shaft is 0.8 μm or less.
5. The extended range power generation system for an aircraft according to claim 1, wherein the oil pump assembly further comprises an oil pump housing, the generator assembly comprises a generator housing, the oil pump housing is arranged at one side of the generator housing in the first direction and forms a containing space for containing the second transmission shaft and the oil duct, the oil pump housing is fixedly connected with the generator housing; the oil pump shell and the generator shell are made of aluminum alloy materials.
6. The extended range power generation system for an aircraft according to claim 5, wherein the oil pump housing and the generator housing are fixedly connected by bolts, and an oil-resistant sealing ring is provided at the connection.
7. The extended range power generation system for an aircraft according to claim 1, wherein the oil pump assembly is a mechanical oil pump comprising an inner rotor and an outer rotor, the inner rotor being rotated by the second drive shaft and eccentrically engaged with the outer rotor to form a variable volume pump chamber inside the oil pump assembly, thereby generating pressure to suck and discharge the coolant.
8. The extended range power generation system for an aircraft according to claim 7, wherein the number of teeth of the inner rotor is 6 to 8 teeth and the number of teeth of the outer rotor is 7 to 9 teeth.
9. The extended range power generation system for an aircraft according to claim 7, wherein the second drive shaft is fixedly connected with the inner rotor through a flat key.
10. An aircraft, characterized in that it comprises an extended range power generation system according to any one of claims 1-9.

Description

Range-extending power generation system for aircraft and aircraft Technical Field The invention relates to the field of aircrafts, in particular to a range-extending power generation system for an aircraft and the aircraft. Background In the context of rapid low-altitude economic development, aviation aircraft (in particular, electric vertical takeoff and landing aircraft, eVTOL) mostly employ range-extending power generation systems. As a core unit, the generator system generates a lot of heat during operation, and an efficient and reliable cooling system must be relied on to ensure operation stability. Because of the stringent requirements of the aircraft on the weight reduction, the compactness and the high reliability of the power assembly, the performance of the cooling system is directly related to the operation efficiency and the flight safety of the whole aircraft. However, existing generator cooling schemes often employ an independent power unit to drive an oil pump, or power coupling through an external transmission structure. This approach not only adds additional drive structure and power components, resulting in a larger overall system volume and increased weight, which makes it difficult to meet the light weight design requirements of an aircraft. Meanwhile, the traditional connection mode is complex to install under the aviation working condition, the transmission efficiency is limited, the problems of ageing of a connecting piece, mechanical abrasion or transmission impact and the like are easy to occur under the vibration environment, the reliability of the system is reduced, and the maintenance cost is high. In addition, because the system integration degree is limited, the layout of the cooling loop is often scattered, and the heat dissipation instantaneity under the high-load working condition is difficult to ensure. There is no better solution to these problems, and there is a need for a new design of extended range power generation system for aircraft. Disclosure of Invention In order to overcome the technical defects, the invention aims to provide an extended-range power generation system for an aircraft and the aircraft. The invention discloses a range-extending power generation system for an aircraft, which comprises a generator component and an oil pump component integrated on one side of the generator component in a first direction; the oil pump assembly comprises a second transmission shaft and an oil duct, wherein the oil duct comprises an oil inlet and an oil outlet, the oil inlet is connected with the generator assembly, and the oil outlet is connected with the heat exchanger; the first transmission shaft and the second transmission shaft are coaxially arranged, and the first transmission shaft and the second transmission shaft are fixedly connected through interference fit, so that when the first transmission shaft rotates, the second transmission shaft is driven to synchronously rotate, and cooling liquid is sucked in through the oil inlet and conveyed to the heat exchanger through the oil outlet for heat dissipation. Preferably, the end part of the first transmission shaft is provided with a matching hole, and the end part of the second transmission shaft is pressed into the matching hole to form interference fit fixed connection. Preferably, the interference fit tolerance of the first and second drive shafts is in the range of 0.02mm to 0.05mm. Preferably, the surface roughness Ra of the mating end surfaces of the first transmission shaft and the second transmission shaft is less than or equal to 0.8 μm. Preferably, the oil pump assembly further comprises an oil pump housing, wherein the generator assembly comprises a generator housing, the oil pump housing is arranged at one side of the generator housing in the first direction and forms an accommodating space for accommodating the second transmission shaft and the oil duct, and the oil pump housing is fixedly connected with the generator housing; the oil pump shell and the generator shell are made of aluminum alloy materials. Preferably, the oil pump shell and the generator shell are fixedly connected through bolts, and an oil-resistant sealing ring is arranged at the connecting position. Preferably, the oil pump assembly is a mechanical oil pump and comprises an inner rotor and an outer rotor, wherein the inner rotor is driven to rotate by a second transmission shaft and is eccentrically meshed with the outer rotor, so that a pump cavity with variable volume is formed in the oil pump assembly, and pressure is generated to suck and discharge cooling liquid. Preferably, the number of teeth of the inner rotor is 6 to 8 teeth, and the number of teeth of the outer rotor is 7 to 9 teeth. Preferably, the second transmission shaft is fixedly connected with the inner rotor through a flat key. A second aspect of the application provides an aircraft comprising an extended range power generation system as claimed in any one of the p