Accession Number : ADB020280


Title :   Eutectic Composite Turbine Blade Development


Descriptive Note : Final technical rept. 1 Apr 1973-30 Nov 1976


Corporate Author : GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP


Personal Author(s) : Brunch, C A ; Haubert, R C ; Gigliotti, M F ; Henry, M F


Full Text : http://www.dtic.mil/dtic/tr/fulltext/u2/b020280.pdf


Report Date : Nov 1976


Pagination or Media Count : 359


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.


Descriptors :   *EUTECTIC COMPOSITES , *GAS TURBINE BLADES , *TURBOJET ENGINES , BENCH TESTS , CARBIDES , COATINGS , COMPUTER PROGRAMS , FATIGUE(MECHANICS) , FIBER REINFORCED COMPOSITES , LIFE EXPECTANCY(SERVICE LIFE) , MACHINABILITY , MECHANICAL PROPERTIES , NICKEL ALLOYS , ORIENTATION(DIRECTION) , OXIDATION , PHYSICAL PROPERTIES , SOLIDIFICATION , TANTALUM ALLOYS , TEST METHODS , THERMAL PROPERTIES


Subject Categories : Aircraft
      Laminates and Composite Materials
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE