Aircraft Engine Automatic Reignition Control
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Solution Overview
Problem
Existing engine reignition methods require manual operator input, which can be complex and inefficient, especially during aircraft flight or when the pilot is absent, and do not effectively address unintended engine shutdowns due to inclement weather conditions.
Innovation Solution
A method and system for automatically reigniting an engine using a fuel purge and ignition sequences, with the engine controller monitoring operating states and speeds to initiate reignition attempts without operator input, employing dry motoring and different ignition sequences based on engine speed thresholds.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If manual reignition is required, then the pilot can control the reignition process, but the operational burden increases and response time is delayed
Solution Approach 1:
The engine controller automatically detects flameout conditions and initiates reignition sequences without requiring pilot intervention. The system monitors engine parameters, determines when flameout has occurred, and executes the appropriate ignition sequence based on current engine state, making the system self-sufficient for the reignition function.
Solution Approach 2:
The system pre-programmes multiple ignition sequences (first and second ignition sequences) with different parameters stored in memory. When flameout is detected, the controller automatically selects and executes the appropriate pre-prepared sequence based on current engine speed and operating conditions, eliminating the need for pilot decision-making.
2Loss of time
If automatic reignition is implemented, then response time is reduced, but system complexity increases
Solution Approach 1:
The system dynamically adapts the ignition sequence based on real-time engine speed. When engine speed is below a threshold, the first ignition sequence is used; when above the threshold, the second ignition sequence is selected. This dynamic adaptation allows a single control system to handle multiple operating conditions effectively.
Solution Approach 2:
The engine controller performs multiple functions: monitoring engine operation for flameout detection, determining current engine state, selecting appropriate ignition sequences, executing the selected sequence, and monitoring for successful reignition. This multi-functionality is achieved within a single control unit rather than requiring separate dedicated systems.
3Reliability
If multiple ignition sequences are used, then reignition success rate improves, but control complexity increases
Solution Approach 1:
The system dynamically adapts the ignition sequence based on real-time engine speed. When engine speed is below a threshold, the first ignition sequence is used; when above the threshold, the second ignition sequence is selected. This dynamic adaptation allows a single control system to handle multiple operating conditions effectively.
Solution Approach 2:
The controller monitors engine parameters to detect flameout conditions and continuously monitors during and after ignition attempts to determine whether reignition was successful. This feedback mechanism allows the system to adapt its behavior based on actual engine state and reignition outcome.
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
Enables automatic and timely engine reignition, reducing the operational burden on pilots and minimizing downtime during engine flameouts, particularly in challenging conditions like inclement weather.
Implementation Method 1
extinction of flames in the combustion chamber
Data Source
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AI summary
Methods (300) and systems (200) for reigniting an engine (100) of an aircraft are described. An engine flameout event is detected during flight. Responsive to detecting the engine flameout event, an engine speed and a commanded engine operating state are monitored. The engine speed is compared to a predetermined threshold. A determination is made regarding whether the commanded engine operating state corresponds to an engine on state. When the commanded engine operating state corresponds to the engine on state, and when the engine speed is below the predetermined threshold, a predetermined ignition sequence for the engine (100) is initiated.