Hybrid Aircraft Propulsion Control for Turbogenerator Overspeed
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Solution Overview
Problem
Hybrid electric aircraft are vulnerable to overspeeding of turbogenerators due to rapid loss of electrical power following circuit breaker openings, which can cause mechanical stress and potential damage, and existing control systems are slow to respond, leading to inefficiencies and design constraints.
Innovation Solution
An electronic control system that receives real-time information on the position of electromechanical protection means, such as circuit breakers, and adjusts fuel flow to anticipate and reduce the overspeed of the turbomachine by rapidly decreasing fuel supply, using an electronic computer and solenoid valve to manage the combustion chamber.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If conventional control systems are used to manage fuel flow in turbogenerators, then the system structure is simple, but the response speed is slow leading to overspeeding and mechanical stress
Solution Approach 1:
The electronic control system receives information about circuit breaker position changes and anticipates the resulting load variation before it fully impacts the turbine. By detecting the open/closed state of circuit breakers and predicting the associated electrical load changes, the system proactively adjusts fuel flow to prevent overspeeding, rather than reacting after the problem occurs.
Solution Approach 2:
The patent replaces conventional mechanical or slow electronic control systems with a modern electronic control architecture that uses electronic sensors, processors, and actuators. The system uses electronic detection of circuit breaker positions and electronic control of fuel metering, substituting slower mechanical linkages and hydraulic systems with faster electronic signal processing and control.
2Reliability
If the control system rapidly decreases fuel supply to prevent overspeeding, then the turbomachine speed is controlled, but the system requires complex sensing and control mechanisms
Solution Approach 1:
The control system continuously monitors the position of electromechanical protection means (circuit breakers) and uses this feedback information to adjust fuel flow. The system establishes a closed-loop control where the state of protection devices directly influences fuel metering, creating a reliable automatic protection mechanism that responds to actual system conditions.
Solution Approach 2:
The electronic control system acts as an intermediary between the electromechanical protection means and the fuel supply system. Rather than directly linking circuit breaker positions to fuel valve actuation through complex mechanical mechanisms, the electronic controller serves as a mediator that receives signals from protection devices and translates them into appropriate fuel flow adjustments.
3Reliability
If redundant systems are designed to protect against overspeeding, then safety is improved, but the weight and complexity of the aircraft increase
Solution Approach 1:
The electronic control system performs multiple functions: it manages normal fuel flow control for power regulation, monitors circuit breaker positions, predicts load variations, and prevents overspeeding. By integrating these diverse functions into a single multi-functional control architecture, the system achieves comprehensive protection without requiring separate dedicated redundancy systems for each function.
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
The system effectively anticipates and reduces the magnitude of overspeed, minimizing mechanical stress on generators and turbines, maintaining functional operation and reducing the need for redundant systems, thus enhancing aircraft performance and safety.
Implementation Method 1
using an electronic computer and solenoid valve to manage the combustion chamber
Implementation Method 2
an internal combustion engine comprising at least one combustion chamber
Data Source
AI summary
A hybrid propulsion installation for an aircraft, including an internal combustion engine having at least one combustion chamber; at least one electricity generator; an electrical propulsion system; electromechanical protection mechanism arranged between the or each electricity generator and the electrical propulsion system; wherein the installation also includes: an electronic computer configured to: receive at least one piece of information on a position of the electromechanical protection mechanism; receive at least one piece of information on a speed of rotation of a shaft of the internal combustion engine; and control the flow of fuel supplying the combustion chamber depending on the information received.