Gas Turbine Sensor Sampling Control for Vibration Events
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Solution Overview
Problem
Existing aircraft sensor systems lack the ability to dynamically adjust data acquisition rates in response to specific vibrational events, leading to inadequate monitoring during engine operation, particularly when vibrational thresholds are exceeded.
Innovation Solution
The system employs micro electro-mechanical systems (MEMS) connected to a controller, which increases the sampling rate of sensors when vibrational thresholds are exceeded, allowing for more frequent data acquisition to compensate for structural vibratory modes, and returns to a base rate once the event subsides.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If the sampling rate is continuously maintained at a high rate to ensure accurate data collection during vibrational events, then measurement precision is improved, but energy consumption increases and productivity decreases
Solution Approach 1:
The system dynamically adjusts the sampling rate based on real-time vibrational conditions. During normal operation, sampling occurs at a base rate to conserve energy. When vibrational events exceed thresholds detected by MEMS sensors, the system automatically increases the sampling rate to capture critical data. This dynamic adaptation resolves the contradiction by making the sampling rate flexible rather than fixed, ensuring measurement precision only when necessary while reducing energy consumption during normal operation.
Solution Approach 2:
The system changes the sampling rate parameter in response to detected vibrational events. The controller monitors parameters such as vibration magnitude and frequency through MEMS sensors, and when threshold violations occur, it modifies the sampling rate parameter from a base rate to an increased rate. This parameter change approach allows the system to maintain measurement precision during critical events while avoiding continuous high-rate sampling that would waste energy.
2Measurement precision
If the sampling rate is increased during vibrational events, then measurement precision is improved, but device complexity increases
Solution Approach 1:
The system segments the monitoring function by placing individual MEMS sensors at specific locations near critical components. Each MEMS sensor independently monitors local vibrational conditions and triggers sampling rate increases only when its local thresholds are exceeded. This segmentation approach improves measurement precision at critical points without requiring a complex centralized system, as each sensor operates semi-independently to control the sampling rate.
Solution Approach 2:
The MEMS sensors act as intermediaries between the physical vibrational environment and the data acquisition system. Rather than directly complexifying the main control system, the patent introduces MEMS sensors as intermediary devices that detect vibrational events and signal the controller to adjust sampling rates. This intermediary approach simplifies the overall architecture by offloading the detection function to specialized sensors while keeping the controller's logic relatively simple.
3Reliability
If multiple MEMS sensors are deployed at different components, then reliability is improved, but device complexity and manufacturing cost increase
Solution Approach 1:
The patent employs identical MEMS sensor designs across multiple components, making each sensor universal and multi-functional. The same MEMS sensor type monitors different components (compressor, combustor, turbine, etc.), eliminating the need for component-specific sensor designs. This universality improves reliability through redundant monitoring capability while reducing device complexity by standardizing the sensor architecture across the entire engine system.
Solution Approach 2:
The system pre-positions MEMS sensors at anticipated problem locations during manufacturing, before actual vibrational events occur. This preliminary placement ensures that sensors are already in optimal positions to detect critical events, improving reliability without requiring complex real-time sensor deployment mechanisms. The sensors are pre-configured to monitor specific components, and their thresholds are set in advance, simplifying the overall system architecture.
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
This solution enables more accurate and timely data collection during vibrational events, improving engine monitoring and potentially reducing maintenance needs by ensuring sufficient data acquisition rates are maintained during critical operational conditions.
Implementation Method 1
a first micro electro-mechanical-system (MEMS) disposed local to a first component within the aircraft system, the first MEMS being communicatively connected to a controller, and being configured to trigger in response to a corresponding parameter exceeding a threshold
Implementation Method 2
the controller to increase a sampling rate of the first sensor to a sampling rate corresponding to the first component for at least a predetermined length of time in response to the first MEMS being triggered
Data Source
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Figure 5
AI summary
An aircraft sensor system (100) includes a first sensor (90; 110; 430) configured to detect a parameter of an aircraft system and a first micro electromechanical-system (MEMS) (120, 122, 124, 126, 128; 410) disposed local to a first component within the aircraft system. The first MEMS (120, 122, 124, 126, 128; 410) is communicatively connected to a controller (92; 130; 420), and is configured to trigger in response to a corresponding parameter exceeding a threshold (232). The controller (92; 130; 420) is connected to an output of the first sensor (90; 110; 430) and includes a non-transitory memory storing instructions configured to cause the controller (92; 130; 420) to increase a sampling rate of the first sensor (90; 110; 430) to a sampling rate corresponding to the first component for at least a predetermined length of time in response to the first MEMS (120, 122, 124, 126, 128; 410) being triggered.