Inconel Alloy Equiaxed Crystal Casting Turbine Components Heat Treatment Company
Optimizing Inconel Turbine Components Through Controlled Heat Treatment
Inconel alloy turbine components produced via equiaxed crystal casting provide reliable high-temperature performance with isotropic grain structures ideal for complex geometries. However, achieving maximum strength, creep resistance, and microstructural stability requires precisely engineered heat treatment processes tailored to each Inconel grade and part geometry.
Neway AeroTech is a specialized heat treatment company for Inconel alloy turbine components. We offer NADCAP-compliant post-casting thermal processing for blades, vanes, nozzle segments, and combustor hardware to meet aerospace and energy industry specifications.
Core Heat Treatment Capabilities for Equiaxed Inconel Castings
Neway AeroTech uses precise temperature control, gas atmosphere monitoring, and multi-stage thermal cycles to enhance microstructure and mechanical properties.
Solution annealing to dissolve segregated phases and homogenize grain boundaries
Aging treatment for controlled gamma prime precipitation and hardness development
Stress relief to minimize distortion before CNC machining
Custom ramp rates to prevent incipient melting and grain coarsening
Processes are tailored to each alloy and validated through metallographic and mechanical testing.
Common Inconel Grades and Applications
Alloy | Max Temp (°C) | Yield Strength (MPa) | Heat Treatment Purpose |
|---|---|---|---|
1050 | 880 | Aging to increase creep resistance | |
950 | 760 | Solution treatment to reduce segregation | |
1000 | 640 | Stress relief prior to welding or CNC | |
980 | 827 | Low-temp aging for structural strengthening |
Alloys are selected for their castability, oxidation resistance, and heat treatment responsiveness.
Case Study: Heat Treatment of Inconel 738 Nozzle Segments
Project Background
A power generation OEM supplied Inconel 738 nozzle castings with moderate porosity and surface dendritic structures. A controlled two-stage heat treatment was applied—solution annealing at 1160°C followed by aging at 845°C for 16 hours. Final microstructure exhibited >60% gamma prime phase with no interdendritic segregation.
Treated Components and Industry Applications
Component | Alloy | Treatment Method | Industry |
|---|---|---|---|
Nozzle Segment | Inconel 738 | Solution + Aging | |
Turbine Blade | Inconel 713C | Stress Relief + Aging | |
Combustor Shield | Inconel 625 | Stress Relief | |
Transition Vane | Inconel 617 | Annealing + Machining |
Each part undergoes process verification through hardness testing, grain structure inspection, and dimensional validation.
Heat Treatment Challenges for Equiaxed Inconel Turbine Components
Gamma prime precipitation control for target hardness and fatigue life
Minimizing distortion during solution annealing in thin-wall geometries
Avoiding incipient melting near the liquidus during high-temp holding
Controlling carbide morphology to prevent grain boundary weakening
Ensuring uniform grain size across shroud, platform, and blade regions
Proven Thermal Treatment Solutions
Solution heat treatment at 1120–1180°C with ±2°C precision control
Aging at 845°C for 8–24 hours depending on component cross-section
Vacuum or argon inert atmosphere to eliminate surface oxidation
HIP prior to heat treatment to remove porosity and improve phase response
Water or air quenching depending on alloy sensitivity
Results and Quality Assurance
Process Execution
Each component received custom thermal profiles based on alloy, geometry, and mechanical specification. Atmosphere control ensured oxidation-free surfaces, and programmable furnaces delivered consistent cycle accuracy.
Metallurgical Results
Post-treatment hardness for Inconel 738 ranged 350–390 HV. SEM confirmed uniform gamma prime precipitation; grain size remained within ASTM 5–7. No carbide agglomeration or residual microsegregation observed.
Final Inspection
CMM inspection verified dimensional stability post-treatment. X-ray ensured no deformation or cracking. SEM analysis validated grain structure and precipitate morphology.
FAQs
What is the standard aging cycle for Inconel 738 cast parts?
Can equiaxed Inconel 713C be treated without warping thin vane sections?
How is heat treatment controlled to prevent incipient melting?
Do you offer HIP + heat treatment packages for turbine parts?
How is phase distribution verified after thermal processing?
