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K919P08 – GE Aviation Stage 9 High Pressure Compressor (HPC) Wide-Chord Blade
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The GE Aviation K919P08 is a high-precision, flight-critical compressor blade engineered for the 9th stage of the High-Pressure Compressor (HPC) in advanced turbofan engines, including the GE90 and GEnx series. As air moves through the compression core, the K919P08 is responsible for increasing the static pressure of the airflow before it enters the final stages of compression and the combustion chamber. The "Wide-Chord" design of this blade represents a significant aerodynamic advancement, providing a larger surface area that improves chord-wise pressure distribution and enhances the engine's stall margin and overall thermal efficiency.
Constructed from a proprietary high-temperature nickel-based superalloy, the K919P08 is designed to operate in the "hot section" of the compressor, where temperatures can exceed $1,000^\circ\text{F}$ ($538^\circ\text{C}$). The blade features a precision-machined dovetail root for secure attachment to the Stage 9 disk, ensuring structural integrity under the massive centrifugal forces generated at core speeds exceeding 10,000 RPM.
Key Features
Advanced Wide-Chord Geometry: Provides a robust aerodynamic profile that resists "flutter" and increases the blade's tolerance to inlet flow distortions, contributing to a more stable engine operating envelope.
High-Temperature Nickel Superalloy: Specifically formulated to maintain high tensile strength and creep resistance in the intense heat and pressure environment of the mid-to-rear HPC stages.
Precision-Matched Dovetail Root: Engineered for a high-tolerance fit into the compressor disk slot, utilizing specialized coatings to prevent fretting fatigue and galling during thermal expansion.
Enhanced Erosion Resistance: The leading edge is profiled and hardened to resist the abrasive effects of "sand-blasting" from atmospheric particulates, extending the blade's effective service life (TBO).
Moment-Weight Calibration: Each K919P08 is precision-weighed and serialized to ensure a perfectly balanced rotor assembly, minimizing N2 shaft vibration.
Technical Specifications
Part Number: K919P08
Manufacturer: GE Aviation (General Electric)
Component Type: Stage 9 HPC Compressor Blade
Design Type: Wide-Chord / Airfoil
Material: Nickel-Based Superalloy (High-Temp)
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: The primary powerplant for the Boeing 777-200LR and 777-300ER.
General Electric GEnx Series: Utilized on the Boeing 787 Dreamliner and 747-8.
Note: Compressor blades are stage-specific and must be installed as part of a balanced set. Always verify the K919P08 against your Engine Illustrated Parts Catalog (EIPC) Section 72-31 to ensure correct dash-number and intermixability status.
Applications
The K919P08 is utilized for Core Air Compression. Its primary roles include:
Static Pressure Increase: Converting kinetic energy from the rotating shaft into potential energy (pressure) to feed the high-pressure turbine.
Thermal Management: Contributing to the overall compression ratio ($P_3/P_2$), which is vital for the fuel efficiency ($\text{SFC}$) of modern ultra-high-bypass engines.
Rotor Stabilization: Providing the necessary aerodynamic damping to maintain smooth core rotation at high power settings.
Why Choose K919P08?
Choosing the genuine GE Aviation K919P08 ensures the Core Health of your engine. In the high-pressure environment of Stage 9, even microscopic deviations in airfoil shape can lead to "vane-passing frequency" harmonics that cause downstream damage to the high-pressure turbine. The K919P08 is manufactured using GE’s proprietary casting and grinding processes, ensuring that the boundary layer airflow remains attached to the blade surface, preventing the aerodynamic stalls that can lead to costly engine surges.
The K919P08 functions as an Axial Flow Work-Blade governed by the Euler Turbomachinery Equation. As the blade rotates, it imparts work ($W$) onto the air, increasing its enthalpy. The "Wide-Chord" design is a response to the physics of Transonic Flow; by increasing the chord length ($c$), GE engineers reduced the aspect ratio, which physically stiffens the blade against aeroelastic instability. This allows the Stage 9 compressor to handle higher mass-flow rates without increasing the risk of mechanical fatigue. The nickel-alloy matrix is specifically designed to resist Thermal Creep—the tendency of metal to slowly deform under constant stress and high heat—ensuring the blade tip clearances remain within the sub-millimeter tolerances required for maximum thrust.
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 a qualified MRO facility. Blades must be mapped to the disk according to the moment-weight chart provided in the Engine Maintenance Manual (EMM).
