Turbine Blade Integrity Analysis for Hypersonic Flight
A leading aerospace manufacturer required a comprehensive failure analysis of a new generation nickel-based superalloy turbine blade. The component, designed for a hypersonic propulsion system, exhibited premature micro-cracking during initial ground testing, threatening a multi-billion dollar development program.
The Challenge
Identify the root cause of sub-surface micro-crack initiation in a single-crystal CMSX-4® alloy blade under simulated high-pressure, high-temperature conditions exceeding 1500°C. The analysis needed to be non-destructive to preserve the integrity of the limited prototype batch.
Our Solution & Process
We deployed a phased analytical protocol, beginning with advanced ultrasonic phased array scanning to map the internal flaw geometry without sectioning the blade.
- Phase 1: High-resolution micro-hardness profiling across the blade's airfoil and root sections.
- Phase 2: Residual stress mapping using X-ray diffraction (XRD) to identify stress concentrations.
- Phase 3: Focused ion beam (FIB) milling for nano-scale SEM analysis of the crack initiation site.
Key Findings & Results
Our analysis pinpointed the failure to a localized thermal gradient during the coating process, which induced a brittle phase transformation at the substrate-coating interface—a flaw not detectable by standard quality control.
99.7%
Detection Accuracy
0.3mm
Flaw Resolution
The detailed report enabled a corrective adjustment to the coating protocol, salvaging the existing prototype batch and preventing an estimated 18-month delay in the project timeline.
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