Aircraft Engine Health Monitoring Using Turbine Temperature Difference
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Solution Overview
Problem
Current methods for monitoring engine health in multiple engine aircraft face challenges due to flight-to-flight variations in operating and ambient conditions, which introduce noise in turbine gas temperature data, making it difficult to accurately assess engine health.
Innovation Solution
The method involves obtaining and standardizing turbine gas temperatures from multiple engines during consistent conditions, such as take-off, and comparing these standardized values to reduce the impact of variations, allowing for more accurate engine health monitoring by defining a value based on the difference between the engines' temperatures and statistically analyzing these values over multiple flights.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If turbine gas temperature data is obtained and normalized for multiple flights, then engine health monitoring capability is improved, but flight-to-flight variations introduce noise that reduces measurement precision
Solution Approach 1:
The patent segments the temperature data analysis by engine type (first engine type vs. second engine type) and by flight phase (take-off vs. other phases). This segmentation allows for separate normalization and comparison within homogeneous groups, reducing the noise from flight-to-flight variations while maintaining the ability to monitor engine health across different flights.
Solution Approach 2:
The patent changes the parameter being monitored from absolute turbine gas temperature to the difference between temperatures of two engines of the same type. This parameter transformation (ΔT = T1 - T2) eliminates common-mode variations affecting both engines equally, thereby improving measurement precision while maintaining reliability.
2Reliability
If temperature normalization is attempted to correct for various conditions, then engine health determination is improved, but significant noise from external factors remains that reduces measurement precision
Solution Approach 1:
The patent extracts and removes the common-mode variations affecting both engines by comparing the difference between two engines of the same type rather than analyzing absolute temperature values. This extraction approach eliminates external factors such as ambient temperature changes and flight conditions that affect both engines similarly, thereby improving measurement precision while maintaining the ability to detect engine-specific health issues.
Solution Approach 2:
The patent introduces the temperature difference (ΔT) as an intermediary parameter that mediates between the absolute temperature measurements and the engine health assessment. This intermediary eliminates the direct influence of external factors while preserving the information needed for health monitoring, resolving the contradiction between reliability and precision.
Data Source
AI summary
Methods for monitoring engine health of an aircraft having a first engine and a second engine are provided. In one example, the method includes obtaining a first turbine gas temperature of the first engine and a second engine turbine gas temperature of the second engine from a first flight. The first turbine gas temperature and the second turbine gas temperature are related to each other to define a first value. The first value is compared to a data set for monitoring the engine health.