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2A9321 – International Aero Engines (IAE) Stage 1 High Pressure Turbine (HPT) Blade
Available now on the Airparts.aero Marketplace.
The IAE 2A9321 is a flight-critical, OEM Stage 1 High Pressure Turbine (HPT) blade specifically engineered for the high-thrust variants of the V2500-A5 and V2500-D5 turbofan engines. Positioned immediately downstream of the combustion chamber, this component is the first rotating stage to encounter the extreme thermal energy of the core exhaust. The 2A9321 is designed to operate in a continuous "white-heat" environment where the ambient gas temperature significantly exceeds the melting point of the blade's base metal, necessitating a sophisticated integration of materials science and active cooling.
As a Stage 1 HPT blade, the 2A9321 must maintain its structural profile while subjected to massive centrifugal forces—upward of 15 tons of pull per blade—at rotational speeds exceeding 10,000 RPM. This specific part number represents an advanced iteration of the V2500 turbine hardware, featuring optimized cooling hole geometries and an improved Thermal Barrier Coating (TBC) to enhance "Time on Wing" and fuel efficiency. It is a Life-Limited Part (LLP) that requires meticulous "back-to-birth" (BTB) traceability.
Key Features
Second-Generation Single-Crystal (SX) Alloy: Cast from a nickel-based superalloy (typically PWA 1484) that lacks grain boundaries, providing exceptional resistance to thermal creep and stress-rupture at temperatures reaching $2,000^\circ\text{F}$ ($1,093^\circ\text{C}$).
Intricate Multi-Pass Cooling: Features an internal "serpentine" labyrinth with pedestals and turbulators that maximize the heat transfer coefficient ($h$) between the metal and the compressor bleed air.
Laser-Drilled Film Cooling: Employs hundreds of precision-angled "showerhead" and "suction-side" cooling holes that eject air to form a protective gaseous boundary layer, insulating the blade from hot gas erosion.
Sputtered Yttria-Stabilized Zirconia (YSZ) TBC: Coated with a ceramic thermal barrier that acts as a physical insulator, reducing the base metal temperature by as much as $300^\circ\text{F}$.
Precision Fir-Tree Attachment: Utilizes a complex, multi-lobed "fir-tree" root design to provide maximum surface area for load distribution into the HPT disk, minimizing the risk of disk-post fatigue.
Technical Specifications
Part Number: 2A9321
Manufacturer: International Aero Engines (IAE)
Component Type: Stage 1 High Pressure Turbine (HPT) Blade
Engine Application: V2527-A5, V2530-A5, V2533-A5 (Airbus A320 Family)
Material: Nickel-Based Single-Crystal Superalloy
Coating: Ceramic Thermal Barrier Coating (TBC) / MCrAlY Bond Coat
Cooling Architecture: Combined Convection, Impingement, and Film Cooling
Certification: FAA-PMA / EASA Form 1 (OEM Certified)
Status: Life-Limited Part (LLP)
Aircraft Compatibility
Airbus A319/A320/A321: Equipped with V2500-A5 SelectOne™ or SelectTwo™ standards.
McDonnell Douglas MD-90: Equipped with V2525-D5 or V2528-D5 variants.
Embraer C-390 Millennium: (V2500-E5 military variant).
Note: HPT blades are installed as moment-weight-matched sets. Refer to the Engine Maintenance Manual (EMM) for specific intermixability and "Stack-Up" limits.
Applications
The 2A9321 is the primary energy-extraction component of the High Pressure Turbine Module. It converts the kinetic and thermal energy of the combusted fuel-air mixture into the high-torque mechanical rotation required to drive the engine’s High Pressure Compressor (HPC) and accessory gearbox.
Why Choose 2A9321?
The 2A9321 is engineered for the highest reliability in the engine's most hostile zone. Choosing genuine IAE 2A9321 blades prevents the catastrophic risk of blade untwist or trailing edge breakout associated with non-standard or improperly repaired hardware. These blades are manufactured to ensure that the internal cooling wall thicknesses are consistent, preventing "hot spots" that can lead to rapid oxidation and uncontained engine failure.
The 2A9321 functions through the principle of Convective and Transpiration Cooling. Because the turbine inlet temperature ($T_{it}$) is significantly higher than the alloy's incipient melting point, the blade relies on a continuous supply of $13^{th}$-stage compressor bleed air. This air enters the root and is forced through an internal labyrinth where it performs impingement cooling on the leading edge. As the air exits through the laser-drilled film holes, it remains attached to the convex and concave surfaces of the airfoil due to the Coandă effect, creating a film of relatively cool air that decouples the metal from the $3,000^\circ\text{F}+$ gas stream. The single-crystal structure is vital here; by eliminating grain boundaries, the blade resists diffusional creep, ensuring the airfoil maintains its aerodynamic "twist" and "tilt" under the relentless centrifugal and thermal loads of cruise flight.
Note: This is a flight-critical, Life-Limited Part (LLP). Installation must be performed at a certified Part 145 Engine MRO facility. Full "Back-to-Birth" (BTB) documentation and non-incident statements are required for airworthiness. Prior to installation, inspect for TBC spallation and ensure all cooling holes are unobstructed by volcanic ash or environmental debris. Installation must comply with the V2500 Engine Maintenance Manual (EMM) Section 72-41-00.
Documentation
No public-facing OEM engineering drawings are available for this ITAR-restricted component; refer to the Engine Component Maintenance Manual (CMM).
