Aircraft Gas Turbine Engine Power Supply Circuit Architecture
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Solution Overview
Problem
Gas turbine airplane engines face challenges in efficiently distributing electricity to various equipment, as traditional systems require multiple generators and complex circuits, and the increasing electrical power demand on airplanes necessitates a more efficient and redundant power distribution architecture.
Innovation Solution
A novel electrical power supply circuit with three buses (DC or AC) connected to a central source, allowing for flexible voltage conversion and redundancy, where the first bus powers low-power equipment, the second bus powers high-power equipment, and both are connected to a third bus for redundancy, with the option to draw power from the airplane's network or a dedicated generator.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional separate generator systems are used for each engine, then each engine can operate independently, but the system complexity and number of components increase
Solution Approach 1:
The patent merges the power supply systems by connecting both engines to a common electrical busbar instead of using separate generators for each engine. This consolidation reduces the total number of generators and circuit components while maintaining the ability of each engine to operate independently through the shared electrical infrastructure.
Solution Approach 2:
The common electrical busbar serves multiple functions: it distributes power to both engines simultaneously, allows either engine to power the other, and provides a centralized point for electrical connections. This multi-functional design eliminates the need for dedicated separate generator systems for each engine.
2Adaptability or versatility
If more electrical equipment is added to the engine, then functional capabilities increase, but the electrical power demand increases requiring larger generators
Solution Approach 1:
By consolidating both engines on a common electrical busbar, the system pools the total power capacity of both engines to meet the combined electrical demands of all equipment. This shared power architecture allows increased equipment versatility without requiring proportionally larger dedicated generators for each engine.
3Reliability
If a dedicated generator is used for each engine, then power supply reliability is improved, but the weight and space requirements increase
Solution Approach 1:
The patent eliminates redundant generator hardware by merging both engines onto a common electrical busbar. This single shared electrical infrastructure provides sufficient power supply reliability for both engines without the weight penalty of duplicating generator systems, directly addressing the weight reduction goal.
4Device complexity
If electrical power is drawn from the airplane network, then the engine can operate with minimal dedicated power sources, but the airplane network must handle increased power demands
Solution Approach 1:
The common busbar architecture merges the power supply capabilities, allowing the combined output of both engines to feed into the airplane network. This distributed power approach reduces the need for large dedicated generators while the network handles the aggregated power demand from both engines and their equipment.
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 enables efficient and redundant electricity distribution to gas turbine engine equipment, reducing the need for specific generators and allowing the engine to operate independently, while minimizing power draw from the airplane's network, which can handle the increased electrical demands without significant drawbacks.
Implementation Method 1
a first bus for distributing DC or AC to first pieces of electrical equipment of the engine, a second bus for distributing DC or AC at higher voltage
Data Source
AI summary
A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power.