Aircraft Jet Engine Fan Blade Damage Detection
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current monitoring systems for aircraft gas turbine engines provide vague feedback on fan blade damage, leading to potential incorrect engine shutdowns and increased risk of engine failure due to ingestion of foreign objects, particularly large birds, and struggle to maintain survivability with lightweight fan blades.
Innovation Solution
A system that automatically determines the safe operating range for gas turbine engines by detecting flutter and blade angle changes using sensors, allowing for power reduction and precise identification of damage, thereby preventing engine failure and ensuring safe operation even after bird strikes or other damage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If lightweight fan blades are used to decrease weight and increase fuel economy, then fuel economy is improved, but the survivability and reliability of the engine after foreign object ingestion deteriorates
Solution Approach 1:
The system performs preliminary detection of blade damage using sensors that monitor blade position and flutter characteristics. By detecting damage early and determining a safe operating range before catastrophic failure occurs, the system enables the engine to continue operating safely with lightweight blades even after foreign object ingestion
Solution Approach 2:
The system continuously monitors blade conditions through sensors and provides feedback to the control system. Based on this feedback, the control system automatically adjusts engine operation to maintain blades within their safe operating range, enabling real-time adaptation to damage conditions and preventing progression to catastrophic failure
2Device complexity
If traditional monitoring systems are used to detect fan blade damage, then device complexity is reduced, but measurement precision and reliability of damage detection deteriorates
Solution Approach 1:
The system uses flutter detection based on vibration characteristics of the fan blades. Sensors detect vibrational patterns that indicate blade damage, and the control system determines safe operating ranges based on these vibration measurements. This approach provides precise damage detection without requiring complex monitoring equipment
Solution Approach 2:
The system replaces complex mechanical monitoring systems with sensor-based detection of blade position and vibration characteristics. By using optical or electrical sensors to detect blade angle and flutter rather than mechanical gauges, the system achieves higher measurement precision with reduced mechanical complexity
3Device complexity
If vague feedback from traditional monitoring systems is provided to pilots, then device complexity is reduced, but the reliability of pilot decision-making and engine operation deteriorates
Solution Approach 1:
The system provides precise, real-time feedback to pilots regarding blade damage conditions and safe operating ranges. Rather than vague indicators, the control system communicates specific operational parameters that keep damaged blades within safe limits, enabling pilots to make accurate decisions about engine operation
Solution Approach 2:
The control system automatically manages engine operation to maintain blades within safe operating ranges based on detected damage conditions. This self-adjusting capability reduces the burden on pilots while ensuring reliable operation, as the system independently optimizes engine parameters based on real-time blade conditions
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 reduces the risk of engine failure by accurately identifying damaged fan blades, allowing for controlled power reduction and maintaining engine operation within safe parameters, even after large bird strikes, while also preventing progressive fatigue cracking and reducing pilot error.
Implementation Method 1
flutter is detected for each of the blades in the fan sections
Implementation Method 2
flutter is detected for each of the blades in the fan sections of each of the gas turbine engines
Implementation Method 3
sensors detect an angle of each blade based upon sensing the arrival of a trailing edge and a leading edge
Data Source
Figure 1A
Figure 1B
Figure 2A~5
AI summary
An aircraft jet engine system includes at least one gas turbine engine (10) having a fan (14) including a rotor and a plurality of fan blades (100). A sensor system (102, 104) in the fan section (14) senses information about the operation of the blades (100) and provides feedback on the condition of each blade (100) to a control (154). The control (154) is programmed to take in the sensed information and identify a safe operating range for the gas turbine engine (10) based upon damage information developed from the sensed information with regard to each of the blades (100). An aircraft jet engine system incorporating a plurality of gas turbine engines (100) wherein safe operating ranges are developed for each of the gas turbine engines is also disclosed as is a method of operating an aircraft jet engine system.