Development of the AGT101 Regenerator Seals PUBLIC ACCESS

[+] Author Affiliations
C. A. Fucinari, J. K. Vallance, C. J. Rahnke

Ford Motor Company, Dearborn, MI

Paper No. 87-GT-173, pp. V002T04A005; 10 pages
  • ASME 1987 International Gas Turbine Conference and Exhibition
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Anaheim, California, USA, May 31–June 4, 1987
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7924-5
  • Copyright © 1987 by ASME


The design and development of the regenerator seals used in the AGT101 gas turbine engine are described in this paper. The all ceramic AGT101 gas turbine engine was designed for 100 hp at 5:1 pressure ratio with 2500F (1371C) turbine inlet temperature.

Six distinct phases of seal design were investigated experimentally and analytically to develop the final design. Static and dynamic test rig results obtained during the seal development program are presented. In addition, analytical techniques are described. The program objectives of reduced seal leakage, without additional diaphragm cooling, to 3.6% of total engine airflow and higher seal operating temperature resulting from the 2000F (1093C) inlet exhaust gas temperature were met.

Copyright © 1987 by ASME
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