A Technology Development Summary for the AGT101 Advanced Gas Turbine Program 870466

Since the program initiation in October 1979, the Garrett/Ford Advanced Gas Turbine Program, designated AGT101, has made significant progress in developing ceramic technology for gas turbine applications. Successful component development has resulted in engine tests with an all ceramic hot section to temperatures up to 2200F (1204C) and full speed operation to 100,000 rpm [turbine rotor tip speed of 2300 ft/sec (701 m/s)]. An 85-hour test was performed on an all ceramic engine at 2200F (1204C) turbine inlet temperature. These engine tests represent important first steps in the development of ceramic materials and technology.
Engine evaluation was preceded by important component development. Activities included aerodynamic component evaluation and development of a high temperature foil bearing to support the ceramic turbine rotor. Development of low leakage regenerator seals and static ceramic seals in this high temperature environment were critical to engine performance. Iterative fabrication, test, analysis, and design development has led to a successful ceramic structures design that will survive the engine normal start transient (peak stress condition) with 25 percent margin. Multifuel capability has been demonstrated in ceramic combustor rig tests. Important material and process development has led to fabrication of ceramic turbine rotors, and subsequent all-ceramic engine test. While feasibility and performance potential have been demonstrated, further activity is needed to advance the technology of structural ceramics to the point where performance and life are demonstrated.


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