Aircraft Engine Power Extraction via Multi-Spool Generator Segmentation
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Solution Overview
Problem
Current aircraft electrical power systems face challenges in efficiently managing increased electrical demands, as traditional methods of power extraction from aircraft engines can affect engine performance and are not seamlessly integrated with the airframe power system, particularly when operating at low power levels or transitioning from hydraulic to electrical loads.
Innovation Solution
The system integrates multiple AC bus generators driven by both high-pressure (HP) and low-pressure (LP) engine spools, with an electrical power extraction controller synchronizing and paralleling their outputs to provide variable frequency AC power, enabling seamless integration with existing aircraft power systems and optimizing engine performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If electrical power is extracted from the HP engine spool, then electrical power generation is improved, but engine performance deteriorates under certain conditions
Solution Approach 1:
The patent segments the power extraction function by providing separate generators on both the HP and LP spools. This allows the electrical power generation function to be divided between two independent sources, so that power can be drawn from the LP spool when HP spool extraction would harm engine performance, while maintaining the ability to draw from HP spool when appropriate.
Solution Approach 2:
The control system dynamically changes the operating parameters by selectively controlling which spool (HP or LP) supplies power to the electrical load based on engine conditions. This parameter change allows optimization of both electrical power generation and engine performance by adapting the power extraction source to current operational requirements.
2Loss of energy
If electrical power is extracted from the LP engine spool, then fuel efficiency is improved, but electrical power control complexity increases
Solution Approach 1:
The patent introduces a control system as an intermediary that manages the complexity of coordinating multiple power sources. This controller acts as a mediator between the HP and LP spool generators and the electrical load, automatically making decisions about power distribution based on engine conditions, thereby hiding the complexity from the operator while achieving optimal fuel efficiency.
Solution Approach 2:
The control system performs multiple functions: it manages power extraction from both HP and LP spools, synchronizes the variable frequency outputs, and optimizes fuel efficiency. This multi-functional approach consolidates the complexity into a single universal controller rather than requiring separate control mechanisms for each function.
3Adaptability or versatility
If multiple generators are integrated with the airframe power system, then adaptability is improved, but integration complexity increases
Solution Approach 1:
The patent extracts the complexity of multi-generator integration by providing separate, independent generator systems on each spool that can operate autonomously. Each generator can be independently connected to or disconnected from the airframe power system, allowing the system to adapt to different operational requirements without requiring complex integrated control of all generators simultaneously.
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 approach enhances fuel efficiency, transient performance, and reduces the load on HP generators, allowing for dynamic and efficient electrical power production while maintaining compatibility with existing airframe power systems, enabling incremental power electronics integration and potential reduction in HP generator capacity.
Implementation Method 1
an electric generator, a device for converting mechanical energy to electrical energy
Data Source
AI summary
An aircraft power system includes an aircraft engine having a plurality of engine spools, a plurality of AC generators driven by at least one spool, wherein each AC generator is independently operational to supply AC power to a respective AC power bus or a respective power electronics module, and at least one generator driven by a different engine spool, wherein the at least one generator is operational to supply additional AC power to each AC power bus in synchronization with each respective AC generator, or to supply additional AC power to each power electronics module in parallel with the AC power delivered to each power electronics module by the plurality of AC generators. The power electronics module(s) are operational to selectively provide either AC or DC power to desired distribution buses. Each AC generator and the at least one generator may be responsive to commands from an electrical power extraction (EPX) controller. At least one generator may be directly driven to provide variable frequency power.