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FW12309 – Rolls-Royce Stage 1 Low Pressure Compressor (LPC) Fan Blade
Available now on the Airparts.aero Marketplace.
The Rolls-Royce FW12309 is a flight-critical, Stage 1 Low Pressure Compressor (LPC) fan blade designed for the Trent series high-bypass turbofan engines. As the first rotating component encountered by incoming air, this fan blade is the primary driver of engine thrust, responsible for accelerating the massive volume of bypass air that provides the majority of the aircraft's propulsive force. The FW12309 represents a pinnacle of wide-chord fan technology, utilizing a hollow-core titanium construction to achieve maximum aerodynamic efficiency while minimizing rotating mass.
Unlike solid blades, the FW12309 employs a sophisticated Superplastic Forming and Diffusion Bonding (SPF/DB) process. This creates a lightweight, honeycomb-like internal structure between two titanium skins, providing the rigidity required to resist centrifugal "untwisting" and the bird-strike resilience mandated by global aviation authorities. This blade is a central component of the Trent engine's "Quiet Technology" suite, featuring a swept-back profile that manages supersonic tip speeds while reducing the noise footprint during takeoff and climb.
Key Features
Wide-Chord Hollow Titanium Construction: Utilizes a diffusion-bonded internal corrugated core to provide extreme structural stiffness at a fraction of the weight of solid titanium alternatives.
Superplastic Formed (SPF) Aerodynamics: The unique "swept" three-dimensional profile is optimized to delay the onset of shock waves at supersonic tip speeds, enhancing fuel efficiency ($\text{SFC}$).
Fretting Resistant Root: Features a precision-machined "curvic" or dovetail root coated with specialized dry-film lubricants (typically molybdenum disulfide) to prevent galling against the fan disc.
High Foreign Object Debris (FOD) Tolerance: Engineered to withstand high-energy impacts from birds or ice while maintaining structural integrity, preventing a "Fan Blade Out" (FBO) event.
Leading Edge Protection: The leading edge is precision-profiled to resist erosion from dust and rain, maintaining the blade's laminar flow characteristics over thousands of flight cycles.
Technical Specifications
Part Number: FW12309
Manufacturer: Rolls-Royce
Component Type: Stage 1 LPC Fan Blade (Wide-Chord)
Engine Application: Rolls-Royce Trent 700 / Trent 800 Series (Verify per Engine Manual)
Material: Titanium Alloy (Ti-6Al-4V)
Construction: Hollow-core, Diffusion Bonded
Weight: Moment-weighted and serialized for specific disc-slot placement.
Certification: FAA / EASA Type Certified as part of the Trent engine assembly.
Aircraft Compatibility
Airbus A330-200/300: Equipped with Rolls-Royce Trent 700 engines.
Boeing 757/777-200/300: Equipped with Rolls-Royce Trent 800 engines.
Note: Fan blades are life-limited components and must be installed in weight-matched, balanced sets. Refer to the Engine Maintenance Manual (EMM) for specific "intermixability" and "moment-weight" mapping.
Applications
The FW12309 is utilized for Primary Thrust and Initial Compression. Its primary roles include:
Bypass Air Acceleration: Driving the 5:1 or higher bypass ratio that generates over 80% of the engine's total thrust.
Core Air Pre-Compression: Acting as the first stage of the Low Pressure Compressor to feed the intermediate and high-pressure sections.
Centrifugal Stabilization: Maintaining the rotational balance of the N1 shaft at speeds exceeding 3,000 RPM.
Why Choose FW12309?
Choosing a genuine Rolls-Royce FW12309 fan blade is the only way to ensure the Vibration Management of the Trent engine remains within limits. The hollow-core technology is proprietary; non-OEM blades cannot replicate the specific frequency response and harmonic damping of the SPF/DB titanium structure. Installing an incorrect or poorly repaired blade can lead to "fan flutter," which causes rapid fatigue of the fan disc and can result in catastrophic engine failure.
The FW12309 operates on the principle of Aerodynamic Energy Transfer governed by the Euler Turbomachinery Equation. Because the tips of the 97-inch to 110-inch diameter fan reach supersonic speeds, the blade is designed with a specific "twist" and "camber" to manage the transonic flow transition. The hollow titanium construction is not merely for weight; it shifts the blade's natural frequency away from the engine's operating RPM ranges, preventing destructive resonance. During operation, the blade undergoes "untwist" due to centrifugal force; the FW12309 is "pre-twisted" in its static state so that it achieves its perfect aerodynamic profile only when at full takeoff power.
Note: This is a flight-critical, serialized 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 a qualified MRO facility. Blades must be mapped to the fan disc according to the moment-weight chart provided in the EMM. Inspect the root coating and leading edge for debonding or FOD prior to installation.
