High-temperature alloy components used in aerospace, turbine, nuclear, and energy systems are subject to extreme thermal loads and fatigue. Internal porosity, often introduced during vacuum investment casting or powder metallurgy, compromises mechanical integrity and creep resistance. Hot Isostatic Pressing (HIP) is a critical post-processing step that eliminates internal voids, refines grain structures, and enhances fatigue life of superalloy parts.
Neway AeroTech provides HIP treatment for complex components made from Inconel, Rene, CMSX, and Hastelloy alloys, ensuring superior thermal, creep, and pressure resistance.
HIP simultaneously applies high temperature and isostatic pressure to remove porosity and improve isotropy in high-performance alloy components.
Temperature range: 900–1260°C depending on alloy
Pressure range: 100–200 MPa via inert argon gas
Duration: 2–4 hours for typical turbine or structural parts
Atmosphere: Argon in vacuum-sealed autoclave chamber
This treatment restores internal cohesion and prepares parts for subsequent heat treatment or coating processes.
Alloy | Max Temp (°C) | Treated Parts | Industry |
|---|---|---|---|
704 | Rotor hubs, seal casings | ||
980 | Turbine blades, nozzles | ||
1140 | First-stage vanes, airfoils | ||
1175 | Combustion shells, sleeves |
HIP enhances structural uniformity for both equiaxed and directionally solidified castings.
A CMSX-4 airfoil exhibited porosity levels of >0.4% from investment casting. The part underwent HIP at 1190°C, 170 MPa for 4 hours. Post-HIP testing confirmed density >99.9%, improved tensile strength at 1000°C, and fatigue life increased by 2.3× under cyclic thermal loading.
Component | Alloy | Process Type | Industry |
|---|---|---|---|
Turbine Nozzle Segment | Rene 88 | Cast + HIP | |
Inner Combustor Ring | Hastelloy X | HIP + TBC | |
Rotor Disk | Inconel 718 | HIP + machining | |
Shroud Block | CMSX-4 | Cast + HIP |
HIP enables defect-free machining and TBC application on these heat-exposed assemblies.
Internal density >99.9% eliminates shrinkage porosity and non-metallic inclusions from cast and powder metallurgy components
Improved creep resistance extends component life under temperatures up to 1150°C in cyclic loading environments
Restores grain boundary cohesion in directionally solidified or equiaxed crystal structures
Prepares internal surfaces for reliable EDM, drilling, and CNC machining post-processing
Reduces scrap rate by up to 40% through salvage of borderline or repairable castings
HIP in argon atmosphere at rated pressure and hold time
Heat treatment for hardness and strength restoration
Optional CNC machining for finishing of airfoils, housings, or flanges
TBC coatings applied for thermal protection
Final inspection including X-ray, CMM, and SEM validation
HIP was applied in a 1.1 m diameter vessel with ±3°C control accuracy and automated gas pressurization. Full traceability maintained.
Porosity reduced to <0.05%. Yield strength at 800°C improved by 12%. Low-cycle fatigue tests confirmed durability gains over baseline parts.
All parts were finish-machined post-HIP and coated where applicable. Tolerances held within ±0.01 mm. Surface prep verified for TBC adhesion.
CMM confirmed dimensional accuracy. X-ray inspection validated internal consolidation. SEM confirmed grain boundary healing and oxide-free microstructure.
What alloys benefit most from HIP processing?
Can HIP be used on both cast and additively manufactured parts?
How does HIP affect subsequent machining or coating steps?
What is the pressure and temperature range typically used?
How is HIP quality validated after processing?