Hybrid-Electric Engine Descent Power Diversion for Rapid Mode Switching
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Solution Overview
Problem
Aircraft hybrid-electric engines face challenges in efficiently operating during descent, particularly in switching between electric and fuel-burn modes, requiring efficient power management to maintain system efficiency and rapid mode resumption.
Innovation Solution
The implementation of a hybrid-electric aircraft system with first and second hybrid-electric engines, each equipped with an electric motor and a supplemental power unit (SPU) configured as a thermal engine paired with a generator, along with a control system that diverts electrical power from the SPU to the second hybrid-electric engine during descent, allowing the first engine to operate at a minimum descent idle level while the second engine is off or in low-power mode.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If one engine is operated in fuel-burn mode and the other is electrically-driven during descent, then fuel consumption is reduced, but the system complexity increases due to power management requirements
Solution Approach 1:
The power management system is segmented into independent control modules: the SPU controller manages thermal engine power generation, while the FADEC controllers independently manage each hybrid-electric engine. This segmentation allows decentralized decision-making, reducing the complexity of centralized power management while enabling fuel-efficient single-engine descent operations.
Solution Approach 2:
The SPU controller autonomously manages the thermal engine to generate electrical power, and the FADEC controllers independently manage their respective hybrid-electric engines. Each controller operates semi-independently, making local decisions without requiring constant centralized coordination, thereby reducing overall system complexity while maintaining fuel efficiency.
2Reliability
If the electrically-operated engine is rapidly switched to fuel-burn mode when needed, then reliability is improved, but the response time and control complexity increase
Solution Approach 1:
The FADEC controllers continuously monitor engine parameters and pre-position the hybrid-electric engines in a state ready for rapid mode transition. During normal electrically-driven operation, the engines maintain readiness conditions that enable immediate switching to fuel-burn mode when reliability is compromised, reducing both switching time and control complexity.
Solution Approach 2:
The SPU controller and FADEC controllers exchange real-time feedback signals to coordinate power delivery and engine response. This feedback mechanism enables the system to detect reliability issues and initiate mode switching automatically, achieving rapid transitions while maintaining simple control architecture through distributed intelligence.
3Loss of energy
If the SPU generates electrical power for the second hybrid-electric engine during descent, then fuel conservation is enhanced, but the SPU system complexity increases
Solution Approach 1:
The SPU thermal engine is merged with the existing hybrid-electric engine architecture, utilizing the same FADEC control infrastructure and power distribution systems. This integration allows the SPU to generate electrical power for the second hybrid-electric engine during descent without requiring entirely separate control systems, thereby enhancing fuel conservation while limiting the increase in overall system complexity.
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 configuration enhances fuel conservation and operational efficiency during descent by ensuring the engine system can rapidly switch to fuel-burn mode when needed, maintaining reliability and reducing fuel consumption.
Implementation Method 1
a supplemental power unit (SPU) configured as a thermal engine paired with a generator and to generate electrical power
Implementation Method 2
a supplemental power unit (SPU) configured as a thermal engine paired with a generator and to generate electrical power
Implementation Method 3
each of which includes an electric motor to drive operations thereof
Data Source
AI summary
A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, each of which includes an electric motor to drive operations thereof, and a supplemental power unit (SPU). The SPU is configured as a thermal engine paired with a generator and is configured to generate electrical power. The first and second hybrid-electric engines are operable normally and off, respectively, with electrical power generated by the SPU being diverted to the electric motor of the second hybrid-electric engine.