Aircraft Engine Flutter Detection With Adaptive Airflow Control
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Solution Overview
Problem
Turbine engines with variable pitch blades are susceptible to aeromechanical instabilities such as flutter, posing significant structural and safety risks due to unpredictable onset and challenging detection.
Innovation Solution
An engine control system with automated instability abatement that detects incipient instability conditions through sensor signals, adjusts modified control parameters for airflow effector devices like variable pitch blades and vanes, and controls them to prevent flutter.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If variable pitch blades are used to affect engine output and fuel consumption, then engine performance and efficiency are improved, but aeromechanical instabilities such as flutter occur posing structural and safety risks
Solution Approach 1:
The system performs preliminary detection of incipient instability conditions through sensor monitoring and analysis before full flutter develops. By detecting early signs of aeromechanical instability and taking preventive action by adjusting blade pitch or other control parameters, the system prevents the development of dangerous vibration amplitudes while maintaining the benefits of variable pitch operation
Solution Approach 2:
The system continuously monitors vibration signals and other parameters from sensors, analyzes them to detect incipient instability, and provides feedback to the control system. This closed-loop feedback enables real-time adjustment of blade pitch or other control parameters to maintain stable operation while optimizing engine performance
2Use of energy by moving object
If variable pitch blades are used to affect fuel consumption, then fuel efficiency is improved, but aeromechanical instabilities such as flutter occur posing structural and safety risks
Solution Approach 1:
The system detects incipient instability conditions before full flutter develops by monitoring vibration signals and analyzing them in real-time. Early detection allows preventive adjustment of blade pitch to maintain fuel efficiency without allowing dangerous vibrations to develop
Solution Approach 2:
Continuous monitoring of vibration and operational parameters provides feedback to the control system, enabling real-time optimization of blade pitch for fuel efficiency while preventing aeromechanical instabilities through automatic control adjustments
3Reliability
If automated instability abatement is implemented through sensor detection and control parameter modification, then aeromechanical instability prevention is improved, but device complexity increases
Solution Approach 1:
The control system performs multiple functions: it monitors engine operation, detects incipient instability conditions, analyzes sensor data, and executes control adjustments. By consolidating these functions into an integrated control system that leverages existing sensors and actuators, the system achieves comprehensive instability prevention without proportionally increasing complexity
Solution Approach 2:
The system uses existing engine sensors and control infrastructure to detect and prevent instabilities autonomously. The control system self-adjusts blade pitch or other parameters based on detected conditions without requiring external intervention, reducing the need for additional specialized components
Data Source
AI summary
An engine for aeromechanical instability abatement includes a sensor configured to capture data from rotating blades of the engine system, a airflow effector device, and an engine controller. The engine controller is configured to control the airflow effector device according to a nominal schedule, detect, based on a signal from the sensor indicating a vibration amplitude of the rotating blades within a frequency band, an incipient instability condition, in response to the incipient instability condition being present, determine a modified control parameter for at least one of the airflow effector device, and control the airflow effector device according to the modified control parameter, deviating from the nominal schedule.