Eutectic Composite Turbine Blade Development
Abstract
The overall program objective was the development of materials, design, and fabrication technology required for the application of eutectic composites in turbine blades for aircraft engines. An MC carbide fiber reinforced eutectic alloy, NiTaC-13 and the low pressure turbine (LPI) blade of J101 engine were selected to demonstrate the high potential of eutectics, by producing an uncooled eutectic blade having a predicted life equal to that predicted for the cooled superalloy blade. A major accomplishment was the scale-up of a laboratory planar front solidification process, required to achieve the aligned fiber composite microstructure, for producing 1-5/8 inch diameter bars and solid J101 LPT blades. Airfoils of the blades were equivalent to bars in microstructure and stress-rupture properties; hence, extensive property data were obtained with aligned fiber material from bars. Nearly all measured longitudinal strength properties of NiTaC are superior to the best conventionally cast superalloys including: ultimate tensile, creep-rupture, thermal fatigue, low cycle fatigue and high cycle fatigue. Because blade dovetails contained misaligned fiber regions, property data were also obtained for this type of material. Preliminary blade life analysis was performed for two J101 LPT uncooled eutectic blade designs, solid and hollow-tip, and the results indicated both were satisfactory. Therefore, sixty oversize solid blades were cast. In a more detailed analysis of the two blade designs, both bare and coated, results indicated that the bare hollow-tip blade design most closely approached blade life goals and that the dovetail was satisfactory.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1976
- Accession Number
- ADB020280
Entities
People
- C. A. Brunch
- M. F. Gigliotti
- M. F. Henry
- R. C. Haubert
Organizations
- General Electric