Chapter 60. Oxidation– and Creep–Enhanced Fatigue of Haynes 188 Alloy–Oxide Scale System Under Simulated Pulse Detonation Engine Conditions

  1. Hau-Tay Lin and
  2. Mrityunjay Singh
  1. Dongming Zhu,
  2. Dennis S. Fox and
  3. Robert A. Miller

Published Online: 26 MAR 2008

DOI: 10.1002/9780470294758.ch60

26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: B: Ceramic Engineering and Science Proceedings, Volume 23, Issue 4

26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: B: Ceramic Engineering and Science Proceedings, Volume 23, Issue 4

How to Cite

Zhu, D., Fox, D. S. and Miller, R. A. (2002) Oxidation– and Creep–Enhanced Fatigue of Haynes 188 Alloy–Oxide Scale System Under Simulated Pulse Detonation Engine Conditions, in 26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: B: Ceramic Engineering and Science Proceedings, Volume 23, Issue 4 (eds H.-T. Lin and M. Singh), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470294758.ch60

Author Information

  1. NASA John H. Glenn Research Center 21000 Brookpark Road, Cleveland, OH 44135

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 2002

ISBN Information

Print ISBN: 9780470375792

Online ISBN: 9780470294758

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Keywords:

  • detonation engine;
  • detonation environments;
  • cycle thermal ;
  • pyrometers;
  • combustion process

Summary

The development of the pulse detonation engine (PDE) requires robust design of the engine components that are capable of enduring harsh detonation environments. In this study, a high cycle thermal fatigue test rig was developed for evaluating candidate PDE combustor materials using a CO2 laser. The high cycle thermal fatigue behavior of Haynes 188 alloy was investigated under an enhanced pulsed laser test condition of 30 Hz cycle frequency (33 ms pulse period, and 10 ms pulse width including 0.2 ms pulse spike). The temperature swings generated by the laser pulses near the specimen surface were characterized by using one-dimensional finite difference modeling combined with experimental measurements. The temperature swings resulted in significant thermal cyclic stresses in the oxide scale/alloy system, and induced extensive surface cracking. Striations of various sizes were observed at the cracked surfaces and oxide/alloy interfaces under the cyclic stresses. The test results indicated that oxidation and creep-enhanced fatigue at the oxide scale/alloy interface was an important mechanism for the surface crack initiation and propagation under the simulated PDE condition.