Turbine Blade Edge Thickness Verification on Unfinished Profiles
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Solution Overview
Problem
The variability in extra lengths on unfinished parts of aircraft turbine engine blades leads to errors in measuring leading and trailing edge thicknesses, causing compliance issues despite the parts being functional.
Innovation Solution
A method to verify the aerodynamic profile compliance by determining and comparing the thickness of real blades with theoretical blades at multiple points along the camber line, using a least-squares superposition function to align and extract relevant thicknesses, focusing only on useful zones rather than excess material zones.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If theoretical extra lengths are used to calculate leading and trailing edge thicknesses on unfinished parts, then the measurement process is simplified, but measurement precision deteriorates due to variability in real extra lengths
Solution Approach 1:
The patent extracts and removes the problematic extra length zones (S2, S3) from the measurement process. By identifying and excluding these variable zones that cause measurement errors, the method focuses only on the useful zones (ZU) where actual thickness measurements should be taken, thereby eliminating the source of precision deterioration while maintaining operational simplicity
Solution Approach 2:
The patent applies preliminary action by pre-defining the useful zones (ZU) and establishing measurement reference points before actual thickness measurement begins. The camber line is constructed and measurement sections are identified in advance, allowing the measurement process to proceed directly on accurate zones without needing to account for variable extra lengths during measurement
2Area of stationary object
If extra length zones are included in thickness measurements, then the complete blade profile is measured, but manufacturing precision deteriorates due to variability in extra lengths causing false non-compliance findings
Solution Approach 1:
The patent extracts the harmful extra length zones (S2, S3) from the measurement domain, separating them from the useful measurement zones (ZU). This extraction ensures that only the functionally relevant portions of the blade profile are measured for compliance verification, eliminating false non-compliance findings caused by variable extra lengths while maintaining focus on the actual manufacturing precision requirements
Solution Approach 2:
The patent applies local quality by assigning different measurement treatments to different zones of the blade profile. The useful zones (ZU) receive precise thickness measurement and compliance verification, while the extra length zones (S2, S3) are explicitly excluded from measurement. This localized approach ensures manufacturing precision is evaluated only where it matters for actual blade performance
3Area of stationary object
If traditional thickness measurement methods are used on unfinished parts, then all zones are covered, but productivity deteriorates due to increased inspection time and false non-compliance results
Solution Approach 1:
The patent extracts and removes the extra length zones (S2, S3) from the inspection process, reducing the total inspection coverage to only the useful zones (ZU). This extraction eliminates time-wasting measurements on zones that do not affect blade performance, directly improving inspection efficiency and productivity while maintaining coverage of all functionally relevant areas
Solution Approach 2:
The patent applies preliminary action by pre-identifying and marking the useful zones (ZU) and measurement reference points before the actual inspection begins. The camber line is constructed in advance and measurement sections are predetermined, allowing inspectors to immediately begin measurements on relevant zones without spending time determining where to measure or dealing with variable extra lengths, thereby significantly improving inspection efficiency
Data Source
AI summary
A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.