Gas Turbine Operating Margin Calculation for Condition-Based Maintenance
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Solution Overview
Problem
Existing systems for verifying the operational power capability of gas turbine engines are inefficient and often lead to premature maintenance, resulting in unnecessary downtime and reduced engine lifespan.
Innovation Solution
A system and method for determining engine operating margins using an engine control system that calculates normalized engine parameters, accounts for installation configurations, and applies correction factors to predict fully deteriorated engine values, allowing for more accurate maintenance scheduling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional operational power checks are used to verify engine capability, then maintenance can be scheduled, but the maintenance is premature leading to unnecessary downtime and reduced engine lifespan
Solution Approach 1:
The system transforms maintenance scheduling from fixed interval-based to condition-based by continuously monitoring engine parameters (ITT, compressor speed, SFC) and comparing them against deterioration models. This parameter change enables precise determination of actual engine health status, preventing premature maintenance while ensuring safety.
Solution Approach 2:
The patent replaces traditional mechanical power checks and manual assessment methods with an electronic control system that uses processors, sensors, and algorithms to automatically monitor engine parameters, calculate operating margins, and determine maintenance needs. This substitution enables more precise and continuous monitoring without engine shutdown.
2Reliability
If traditional power checks are performed frequently to ensure engine capability, then safety is maintained, but engine utilization is reduced due to premature maintenance
Solution Approach 1:
The engine control system performs self-diagnosis and self-assessment by continuously monitoring its own parameters (ITT, compressor speed, fuel consumption) and comparing them against expected performance models. This self-service capability eliminates the need for frequent external power checks, maintaining safety while maximizing utilization.
Solution Approach 2:
The system implements continuous feedback loops where engine parameters are monitored, compared against deterioration models, and used to dynamically adjust maintenance scheduling. This feedback mechanism ensures engine capability is verified only when necessary, optimizing both safety and productivity.
3Measurement precision
If normalized engine parameters are calculated with correction factors, then measurement precision improves, but device complexity increases
Solution Approach 1:
The engine control system performs multiple functions using the same hardware platform: it monitors engine parameters, calculates normalized values, applies correction factors, predicts deterioration, and schedules maintenance. This multi-functionality reduces overall system complexity compared to having separate systems for each function.
Solution Approach 2:
The system transforms raw sensor data into meaningful diagnostic information by applying normalization and correction algorithms. This parameter transformation enables accurate cross-engine comparison and deterioration tracking without requiring complex additional hardware.
Data Source
AI summary
A system for a gas turbine engine includes an engine control system. The engine control system includes a processor and a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: obtain a current engine installation configuration for the gas turbine engine and the aircraft, determine an expected normalized value of the engine parameter based on the current engine installation configuration and one or more of a normalized engine power (SHPN) of the gas turbine engine, an engine inlet temperature, an airspeed, or an altitude, determine a fully deteriorated engine (FDE) value of the engine parameter using the expected normalized value of the engine parameter, determine a current value of the engine parameter for the gas turbine engine, and determine the engine operating margin for the engine parameter based on the FDE value of the engine parameter and the current value of the engine parameter.