Accession Number : ADA261112


Title :   Field Evaluation of Six Protective Coatings Applied to T-56 Turbine Blades after 2000 Hours of Engine Use


Descriptive Note : Technical rept.


Corporate Author : AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)


Personal Author(s) : Russo, S G


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a261112.pdf


Report Date : Nov 1992


Pagination or Media Count : 39


Abstract : The first-stage high-pressure turbine blades in RAAF T-56 engines have a rejection rate which is unacceptably high. It has been revealed (1) that the current coating, a conventional nickel aluminide, has a greater than 60% rejection rate after 2000 hours. Consequently, a trial programme was established to assess the benefits of five alternative protective coatings and to determine which coatings, if any, could withstand up to 3000 engine operating hours. A previous report demonstrated the potential of platinum and platinum/rhodium modified aluminides after 1500 hours of engine operation. This report, after approximately 2000 hours of service, supports the previous recommendations that the precious metal aluminides offer superior resistance to hot corrosion than the conventional aluminides and chromium-modified aluminides. The inability of the silicon-modified aluminide to form an evenly distributed coating over the entire blade renders it unsuitable.... Protective coatings, Hot corrosion, Allison T56 engines, Gas turbine blades.


Descriptors :   *MICROSTRUCTURE , *GAS TURBINES , *TURBINE BLADES , *CORROSION RESISTANCE , *PROTECTIVE COATINGS , *GAS TURBINE BLADES , *ALUMINIDES , TEST AND EVALUATION , METALS , HIGH RATE , CORROSION , RESISTANCE , STRUCTURAL ANALYSIS , FIELD TESTS , HIGH PRESSURE , SILICON , PRESSURE , ENGINES , PLATINUM , NICKEL , AUSTRALIA , BENEFITS , REJECTION , PRECIOUS METALS , RHODIUM


Subject Categories : Coatings, Colorants and Finishes
      Properties of Metals and Alloys
      Hydraulic and Pneumatic Equipment


Distribution Statement : APPROVED FOR PUBLIC RELEASE