H1127-0101 | ​single-crystal nickel superalloy turbine blade

Rolls-Royce H1127-0101
(High-Pressure Turbine Blade for Aerospace Engines)

​Product Overview

The ​Rolls-Royce H1127-0101 is a ​single-crystal nickel superalloy turbine blade designed for high-pressure turbine (HPT) stages in Rolls-Royce ​Trent series turbofan engines (e.g., Trent 1000, Trent XWB). This critical component withstands extreme temperatures (>1,500°C) and rotational stresses in jet engines, ensuring optimal performance and longevity in commercial aviation, military, and industrial gas turbine (IGT) applications.

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Description

​Key Features

  • ​Material Science:
    • ​Single-Crystal Nickel Superalloy (e.g., CMSX-4®) for creep resistance.
    • ​Thermal Barrier Coating (TBC): Yttria-stabilized zirconia (YSZ) coating for thermal insulation.
    • ​Internal Cooling Channels: Complex serpentine passages for active air cooling.
  • ​Aerodynamic Design: Optimized airfoil geometry to maximize efficiency and reduce aerodynamic losses.
  • ​Certifications: Compliant with EASA/FAA regulations and Rolls-Royce ​RR Standard Practices (RRES SP).

​Technical Specifications

​Parameter ​Details
​Operating Temp Up to 1,700°C (gas path)
​Cooling Efficiency Reduces blade surface temp by 300–400°C
​Frequency Resistance Engineered to avoid resonant frequencies
​Coating Thickness 150–300 µm (TBC + bond coat)
​Weight ~0.5–1.2 kg (varies by engine model)
​Certifications EASA Part 21G, FAA AC 21-40

​Application Areas

  • ​Commercial Aviation: Used in ​Trent 1000 engines (Boeing 787) and ​Trent XWB (Airbus A350).
  • ​Military: Integrates into ​Adour Mk 951 engines (Hawk trainer jets).
  • ​Power Generation: Fits industrial turbines like the ​RB211 for LNG compression and power plants.
  • ​Marine Propulsion: Adapted for MT30 gas turbines in naval vessels.

H1127.0101

​Manufacturing & Maintenance

  1. ​Production: Fabricated via ​investment casting with directional solidification.
  2. ​Coating Process: Applied via ​electron beam physical vapor deposition (EB-PVD).
  3. ​Inspection: NDT methods (X-ray, FPI) to detect micro-cracks and coating delamination.
  4. ​Repair: Refurbished via ​laser cladding or ​TBC reapplication at Rolls-Royce-approved MRO facilities.

​Related Components

  1. ​H1127-0201: Adjacent turbine blade with modified cooling geometry.
  2. ​RR TURBINE DISK: Forged nickel alloy disk (e.g., Inconel 718) for blade mounting.
  3. ​Trent Combustor Liners: Compliant with HPT stage thermal profiles.
  4. ​RR Aerospace Seals: Ceramic matrix composite (CMC) seals for blade tip clearance control.

​Why It Matters

The ​H1127-0101 is pivotal to engine efficiency and safety, directly impacting fuel burn, emissions, and operational lifespan. Its failure modes (e.g., thermal fatigue, oxidation) are critical focus areas in predictive maintenance programs.

​Supply Chain & Compliance

  • ​OEM Source: Rolls-Royce plc (Derby, UK, or Singapore MRO hub).
  • ​Aftermarket: Available via Rolls-Royce ​TotalCare® program or certified distributors.
  • ​Traceability: Each blade includes a ​data matrix code for lifecycle tracking (manufacture, repair, retirement).

​Support

For technical specifications, consult ​Rolls-Royce RRES 90001 documentation or contact ​Customer Technical Services (CTS). Unauthorized repairs void warranties and airworthiness certifications.

Note: Exact dimensions and material specs are proprietary; consult Rolls-Royce for engine-specific validation.

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