Cooled Electric Power Bus for High-Altitude Aircraft Propulsion
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Solution Overview
Problem
Conventional hybrid-electric aircraft propulsion systems face challenges in providing sufficient electrical power to electric fans at high altitudes due to reduced ambient air pressure, making it difficult to transmit high levels of electrical power effectively.
Innovation Solution
The implementation of a cooled electric power bus with a fluid cooling system that extends along the electric line and is in thermal communication with both the electric line and the electric motor, utilizing a fluid cooling conduit and a heat exchanger to maintain efficient power transmission and cooling, thereby enhancing the propulsion system's ability to deliver electrical power.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If high levels of electrical power are transmitted to the electric fan, then the propulsion system can provide sufficient thrust, but the electric line and motor overheat due to resistance losses
Solution Approach 1:
A fluid cooling system acts as an intermediary between the electric power transmission components and the thermal environment. The cooling fluid circulates through conduits in thermal communication with the electric line and motor, absorbing excess heat and transporting it away from the power transmission path, thereby enabling high power transmission without overheating
Solution Approach 2:
The patent employs a hydraulic cooling system where a fluid circulates through cooling conduits to remove heat from the electric line and motor. This hydraulic approach efficiently manages the thermal load generated during high-level electrical power transmission, allowing the system to maintain operational temperatures even at elevated power levels
2Loss of energy
If the electric line is cooled to maintain low temperature, then resistance losses are reduced and power transmission efficiency is improved, but the system complexity increases due to the cooling infrastructure
Solution Approach 1:
The fluid cooling system is designed to serve multiple functions simultaneously: it cools the electric line, cools the motor, and can be integrated with existing aircraft hydraulic or cooling systems. This multi-functionality reduces the need for separate cooling systems for each component, thereby limiting the increase in overall system complexity while achieving effective thermal management
Solution Approach 2:
The cooling conduits are integrated with the electric power transmission line structure, merging the thermal management function with the electrical connection structure. This integration reduces the number of separate components and simplifies the overall system architecture, minimizing the complexity increase associated with adding cooling capabilities
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution ensures reliable and efficient power delivery to the electric propulsor assembly, even at high altitudes, by maintaining the electric line and motor within a desired temperature range, reducing resistance losses and enabling higher power transmission levels.
Implementation Method 1
The fluid cooling system is in thermal communication with the electric line for cooling the electric line during operation
Implementation Method 2
The fluid cooling system is in thermal communication with the electric motor of the electric propulsor assembly for cooling the electric motor
Implementation Method 3
The fluid cooling system further includes a heat exchanger in fluid communication with the fluid cooling conduit
Data Source
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AI summary
A propulsion system 300 for an aircraft 10 includes an electric power source 302, an electric propulsor assembly 304 having an electric motor 312 and a propulsor 314 configured to generate thrust for the aircraft 10, and a power bus 306 electrically connecting the electric power source 302 to the electric propulsor assembly 304 such that the electric power source 302 powers the electric propulsor assembly 304. The power bus 306 includes an electric line 316 and a fluid cooling system 318, the fluid cooling system 318 extending along at least a portion of a length of the electric line 316. The fluid cooling system 318 is in thermal communication with the electric line 316 for cooling the electric line 316 during operation and is further in thermal communication with the electric motor 312 of the electric propulsor assembly 304 for cooling the electric motor 312 of the electric propulsor assembly 304.