Resonance Spectra Inspection for Aircraft Component Defect Detection
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing non-destructive testing methods for aircraft propulsion system components are inadequate in accurately identifying internal defects such as cracks and voids, particularly in rotor disks, due to limitations in detecting structural modes and interpreting vibratory response signatures.
Innovation Solution
A resonance inspection system utilizing a control assembly with a processing system that generates multiple resonance spectra waveforms from vibratory responses, identifying structural modes by analyzing peaks and slope points within specific frequency ranges, and detecting internal defects by comparing these waveforms to known models.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If existing non-destructive testing methods are used to inspect aircraft propulsion system components, then the inspection process is simple and quick, but the accuracy in detecting internal defects such as cracks and voids is insufficient
Solution Approach 1:
The patent segments the vibratory response signature into multiple resonance spectra waveforms (magnitude spectra, phase spectra, real spectra, imaginary spectra) and analyzes each waveform separately for specific features. This segmentation allows the system to extract defect information from different characteristics of the vibratory response, thereby improving defect detection accuracy while managing system complexity through structured analysis.
Solution Approach 2:
The patent transitions from analyzing a single vibratory response signature to generating and analyzing multiple resonance spectra waveforms representing different dimensions of the response (magnitude, phase, real, imaginary parts). This multi-dimensional analysis approach enables more comprehensive defect detection by examining the vibratory response from multiple spectral perspectives simultaneously.
2Measurement precision
If resonance inspection system generates multiple resonance spectra waveforms and analyzes peaks and slope points, then the internal defect detection accuracy is improved, but the inspection time and processing complexity increase
Solution Approach 1:
The patent performs preliminary generation of multiple resonance spectra waveforms from the vibratory response signature before detailed defect analysis. By pre-processing the data into standardized spectral representations (magnitude, phase, real, imaginary spectra), the system prepares the information in advance, enabling faster and more efficient defect detection during the actual inspection process without requiring repeated complex calculations.
Solution Approach 2:
The patent transforms the vibratory response signature into multiple resonance spectra waveforms by changing the parameter representation from time-domain or frequency-domain signals to spectral domain representations with different characteristics (magnitude, phase, real, imaginary parts). This parameter transformation enables the system to identify structural modes and defects by analyzing specific features (peaks, slope points) in the spectral domain, improving accuracy while managing processing time through efficient spectral analysis.
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
Enables accurate and efficient detection of internal defects in aircraft propulsion system components with minimal downtime and cost, facilitating early identification of anomalies that affect performance and lifespan.
Implementation Method 1
The probe may include at least one piezoelectric transducer electrically connected with the control assembly. The instructions, when executed by the processor, may further cause the processor to control the at least one piezoelectric transducer to apply a vibration to the component and measure the vibratory response signature of the component with the at least one piezoelectric transducer.
Implementation Method 2
The processing system includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to process resonance data including a vibratory response signature of a component over a portion of a frequency range of the vibratory response signature to generate a plurality of different resonance spectra waveforms
Data Source
AI summary
A resonance inspection system includes a processing system. The processing system is configured to process resonance data including a vibratory response signature of a component to generate a plurality of different resonance spectra waveforms. The plurality of different resonance spectra waveforms includes a first resonance spectra waveform and a second resonance spectra waveform. The processing system is further configured to identify a presence or an absence of a structural mode of the component using the first resonance spectra waveform and the second resonance spectra waveform. The presence of the structural mode is identified by determining the first resonance spectra waveform includes a peak at a first frequency of the portion of the frequency range and the second resonance spectra waveform includes a maximum or a minimum slope point at a second frequency of the portion of the frequency range. The first frequency and the second frequency are within a predetermined frequency range threshold.