Published: Jan 1976
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The high-pressure, high-temperature turbine test rig was designed for the National Aeronautics and Space Administration to test turbine components in an environment that simulates current and future gas turbines operating at 41 atm (600 psi) and 2204°C (4000°F). This paper illustrates the design approach that led to selection of a typical test rig component: the turbine disk. The final configuration of the rotor assembly and the turbine disk was determined by analysis of low-cycle fatigue and creep.
thermal fatigue, creep (materials), disks, thermal cycling tests, plastic analysis, substructures, turbines
Senior engineering specialist, Applied Mechanics Group, AiResearch Manufacturing Company of California, Torrance, Calif.
Paper ID: STP27883S