NASA Technical Reports Server (NTRS) : The pdf

NASA Technical Reports Server (NTRS) : The

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Gas turbine engines for future subsonic transports will probably have higher pressure ratios which will require nickelbase superalloy disks with 1300 F to 1400 F temperature capability. Several advanced disk alloys are being developed to fill this need. One of these, CH98, is a promising candidate for gas turbine engines and is being studied in NASA’s AST Program. For AST applications, compressor/turbine disks must withstand temperatures of 1300 F for several hundred hours over the life of the engine. Additions of the refractory elements tungsten and niobium to CH98 could improve tensile and creep properties, however, the impact on high temperature fatigue crack growth is uncertain. In this paper, these three key properties, tensile, 0.2 percent creep, and fatigue crack growth of CH98 with and without tungsten and niobium additions will be assessed at l300 F

• Creator/s: NASA Technical Reports Server (NTRS
• Date: 8/1/2003
• Year: 2003
• Book Topics/Themes: NASA Technical Reports Server (NTRS), GAS TURBINE ENGINES, NICKEL ALLOYS, HEAT RESISTANT ALLOYS, THERMAL FATIGUE, TUNGSTEN, NIOBIUM, TENSILE PROPERTIES, CREEP PROPERTIES, CRACK PROPAGATION, Gayda, John

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