Hybrid Turbine Engine Control Using Precharged Capacitor Assist
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Solution Overview
Problem
Conventional aircraft turbomachines face challenges in providing rapid and efficient electrical energy assistance due to the need for high-capacity electrical energy sources and associated electrical losses, which increase footprint and reduce system stability and durability.
Innovation Solution
A method for controlling a hybrid turbomachine using capacitive components pre-charged to maximum voltage before flight, balanced for homogeneous voltage distribution, and rapidly converted into mechanical energy to assist aircraft maneuvers, with a power conversion device on the high-pressure shaft and an energy storage assembly on the low-pressure shaft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a conventional gas turbine engine is modified to operate in hybrid mode with separate control systems for gas turbine and steam turbine modes, then the engine can achieve versatile operation in both modes, but the control system complexity increases and mode transition control becomes difficult
Solution Approach 1:
The patent merges the gas turbine mode control and steam turbine mode control into a single unified control system. The controller integrates both control functions, eliminating the need for separate control systems and reducing overall control system complexity while maintaining the ability to operate in both hybrid and standalone modes.
Solution Approach 2:
The control system is designed with multi-functionality to handle both gas turbine and steam turbine operations, as well as mode transitions between them. The controller can adaptively switch between different control strategies based on the current operating mode, making a single control system capable of performing multiple functions that previously required separate dedicated systems.
2Reliability
If separate control systems are used for gas turbine mode and steam turbine mode, then each mode can be optimized independently, but the mode transition control becomes difficult and response time increases
Solution Approach 1:
The unified control system is pre-programmed with transition protocols and parameters for switching between gas turbine and steam turbine modes. By having the control logic and transition parameters prepared in advance within the single controller, the system can execute mode transitions quickly and smoothly without the delays associated with coordinating between separate control systems.
Solution Approach 2:
The control system incorporates feedback mechanisms that monitor the current operating state and automatically adjust control parameters during mode transitions. This real-time feedback allows the unified controller to detect when a transition is needed and execute it optimally, reducing transition time while maintaining operational reliability.
3Device complexity
If the engine is designed for dedicated gas turbine or steam turbine mode, then the structure can be simplified, but the engine loses the ability to operate in hybrid mode and reduces versatility
Solution Approach 1:
The engine is designed with dynamic configurability, allowing it to adapt its operational characteristics based on the desired mode. The control system can dynamically adjust parameters such as valve positions, flow rates, and power distribution to optimize performance for gas turbine mode, steam turbine mode, or hybrid mode, enabling a single structure to serve multiple functions without requiring separate dedicated designs.
Data Source
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AI summary
The invention relates to a method for controlling a hybrid turbine engine (11) for an aircraft, the turbine engine (11) comprising a low-pressure shaft (10), a high-pressure shaft (9), at least one power conversion device (13) mounted on the low-pressure shaft (10) or the high-pressure shaft (9) and an energy storage assembly comprising a plurality of capacitive components (15), the method comprising the steps of: - precharging the capacitive components (15) until a mean voltage reaches a first partial charging value, - balancing the voltages of the capacitive components (15), - charging the capacitive components (15) until the mean voltage reaches a high value, and - converting electrical energy stored in the storage assembly into mechanical energy delivered to the low-pressure shaft (10) and/or to the high-pressure shaft (9) to assist manoeuvering of the aircraft.