Gas Turbine Engine Lifing Using Actual Flight Damage Data
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Solution Overview
Problem
Current methods for estimating the life of gas turbine engine components are overly conservative and do not account for varying flight conditions, leading to inaccurate damage assessment and premature component replacement.
Innovation Solution
A system that monitors actual flight data, including ambient temperature, internal pressures, and speeds, to develop and apply usage-based lifing algorithms that assess damage accumulation and recommend future component usage to maximize remaining life.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conservative design flight cycles are used for all flights, then component safety is ensured, but component replacement occurs prematurely and maintenance costs increase
Solution Approach 1:
The patent applies parameter changes by transitioning from a uniform cycle counting approach to a continuous monitoring approach that measures actual operational parameters (temperature, pressure, vibration, speed) in real-time. This allows the damage accumulation model to reflect actual component stress conditions rather than assuming all cycles are equal, thereby extending component life while maintaining safety
Solution Approach 2:
The system implements feedback by continuously monitoring component condition parameters and comparing them against damage thresholds. The monitoring system provides real-time data on actual component stress and damage accumulation, which feeds back into the replacement decision process, allowing dynamic adjustment of maintenance schedules based on actual component health rather than fixed cycle counts
2Device complexity
If uniform cycle counting is applied to all flights, then simplicity is maintained, but measurement precision of actual component damage is reduced
Solution Approach 1:
The patent replaces the simple mechanical cycle counting system with an electronic monitoring and computational system. Instead of using a mechanical counter that increments with each flight, the system uses sensors, data acquisition equipment, and damage accumulation algorithms to continuously measure and calculate actual component stress and damage, significantly improving measurement precision
Solution Approach 2:
The system transitions from a static cycle counting method to a dynamic monitoring approach where damage accumulation is continuously updated based on real-time operational conditions. The damage model dynamically adjusts based on actual temperature, pressure, vibration, and speed parameters experienced by the component during each operational phase
3Ease of operation
If all flights are counted as one cycle, then ease of operation is maintained, but loss of information about actual flight conditions occurs
Solution Approach 1:
The patent applies segmentation by dividing the flight profile into multiple distinct phases (takeoff, climb, cruise, descent, landing) and assigning different damage weights to each phase based on actual component stress conditions. This segmented approach preserves detailed flight condition information while maintaining operational simplicity through automated phase identification and damage calculation
Data Source
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AI summary
A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d).