AGT101 Advanced Gas Turbine Technology Update PUBLIC ACCESS

[+] Author Affiliations
G. L. Boyd, J. R. Kidwell, D. M. Kreiner

Garrett Turbine Engine Company, Phoenix, AZ

Paper No. 86-GT-305, pp. V002T04A013; 11 pages
  • ASME 1986 International Gas Turbine Conference and Exhibit
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Dusseldorf, West Germany, June 8–12, 1986
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7929-0
  • Copyright © 1986 by ASME


The Garrett/Ford Advanced Gas Turbine Technology Development Program, designated AGT101, has made significant progress during 1985 encompassing ceramic engine and ceramic component testing. Engine testing has included full speed operation to 100,000 rpm and 1149C (2100F) turbine inlet temperature, initial baseline performance mapping and ceramic combustor start and steady state operation. Over 380 hours of test time have been accumulated on four development engines. High temperature foil bearing coatings have passed rig test and a thick precious metal foil coating selected for engine evaluation.

Ceramic structures have been successfully rig tested at 1371C (2500F) for over 27 hours. Interface compatibility testing conducted during these runs indicate RBSN-to-RBSN or SASC-to-SASC result in “sticking” — however, RBSN-to-SASC in either planar or line contact show no evidence of sticking. Ceramic combustor rig tests have demonstrated acceptable lightoffs using either a conventional ignitor or a commercially available glow plug. Operation to 1371C (2500F) combustor discharge temperatures have also been demonstrated. Ceramic turbine rotor fabrication efforts have continued at ACC and Ford. Kyocera and NGK-Locke also have been working on the rotor. Several rotors have been received and are currently undergoing final machining and qualification tests. Testing of the all-ceramic AGT101 engine is currently scheduled for late 1985.

Copyright © 1986 by ASME
Topics: Gas turbines
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