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K333P08 – GE Aviation Stage 3 High Pressure Compressor (HPC) Wide-Chord Blade
Available now on the Airparts.aero Marketplace.
The GE Aviation K333P08 is a high-performance, flight-critical compressor blade engineered for the 3rd stage of the High-Pressure Compressor (HPC) in modern high-bypass turbofan engines, specifically the GE90 and GEnx families. Situated in the forward section of the high-pressure core, the Stage 3 blade is responsible for the early-stage axial compression of air as it transitions from the low-pressure booster into the high-energy core. The "Wide-Chord" design of the K333P08 is a hallmark of GE’s advanced propulsion technology, providing increased structural rigidity and aerodynamic efficiency without the need for mid-span shrouds.
Constructed from a specialized titanium alloy (typically Ti-6Al-4V or similar high-strength aerospace titanium), the K333P08 is designed to handle the massive centrifugal loads and moderate thermal environment of the forward HPC. Its wide-chord geometry significantly improves the blade's Foreign Object Debris (FOD) tolerance and stall margin, ensuring stable engine operation during rapid power transitions and high-alpha flight maneuvers.
Key Features
Wide-Chord Aerodynamic Profile: Features a broader chord length ($c$) that eliminates the need for damping "snubbers," reducing aerodynamic drag and improving the stage's overall pressure ratio.
High-Strength Titanium Construction: Optimized for the front-end HPC environment where high tensile strength and low weight are required to minimize the rotational inertia of the N2 spool.
Precision-Ground Dovetail Root: Features a high-tolerance mounting base designed to slide into the Stage 3 compressor disk, utilizing specialized anti-fretting coatings (such as Cu-Ni-In) to prevent wear during thermal cycling.
Aeroelastic Stability: Engineered to resist "fan flutter" and harmonic resonance, providing a "quiet" and vibration-free compression path at core speeds exceeding 10,000 RPM.
Leading Edge Durability: The blade's leading edge is precision-contoured to maintain laminar flow even after thousands of cycles, resisting the microscopic erosion caused by atmospheric dust and moisture.
Technical Specifications
Part Number: K333P08
Manufacturer: GE Aviation (General Electric)
Component Type: Stage 3 HPC Compressor Blade
Design Type: Wide-Chord / Shroudless Airfoil
Material: Aerospace Grade Titanium Alloy
Root Interface: Dovetail
Engine Application: GE90-115B, GEnx-1B/2B (Verify per Engine Manual)
Certification: FAA / EASA Type Certified Engine Component
Engine Compatibility
General Electric GE90 Series: Powering the Boeing 777-200LR, 777-300ER, and 777F.
General Electric GEnx Series: Powering the Boeing 787 Dreamliner and 747-8.
Note: The K333P08 is stage-specific. Always verify the part number and "intermixability" status in the Engine Illustrated Parts Catalog (EIPC) Section 72-31 to ensure it matches your specific rotor serial number.
Applications
The K333P08 is utilized for Initial Core Compression. Its primary roles include:
Pressure Multiplication: Significantly increasing the air density as it enters the mid-stages of the high-pressure core.
Flow Direction: Guiding compressed air into the Stage 4 stator vanes with minimal turbulence.
Inertial Balance: Contributing to the overall mass-balance of the HPC rotor assembly to ensure smooth N2 shaft operation.
Why Choose K333P08?
Choosing the genuine GE Aviation K333P08 is essential for maintaining the Stall Margin of the engine. In the forward HPC stages, aerodynamic "stalls" can lead to catastrophic engine surges. The K333P08 is manufactured using GE’s proprietary 3D-aero design software, ensuring the Pressure Coefficient across the blade surface is perfectly managed. Furthermore, the titanium alloy used in the K333P08 is specifically "grained" during the forging process to prevent Stress Corrosion Cracking (SCC), a common failure mode in non-OEM or sub-standard compressor hardware.
The K333P08 functions on the principle of Axial Work Transfer. In a turbine engine, the compressor does work on the air to increase its potential energy ($P$). The Stage 3 environment is particularly sensitive to Centrifugal Untwist—the tendency of a blade to straighten its aerodynamic twist under high RPM. The K333P08 is "pre-twisted" in its cold, static state so that it reaches its ideal aerodynamic camber only when operating at cruise RPM. This ensures that the Angle of Attack remains optimal across the entire span of the blade, from root to tip, maximizing the compression efficiency of the GE90/GEnx core.
Note: This is a flight-critical, serialized engine component. Full "Back-to-Birth" (BTB) documentation and non-incident statements are required for airworthiness. Installation must be performed by a certified powerplant mechanic at an authorized MRO facility. Blades must be mapped and installed in weight-matched sets according to the Engine Maintenance Manual (EMM).
