Chapter 16. Design Conceptualization of Air-Cooled Coated Silicon Nitride Plates for Gas Turbine Applications

  1. Hua-Tay Lin and
  2. Mrityunjay Singh
  1. Morris M. Girgis1,
  2. Ramakrishna T. Bhatt2 and
  3. Ali Abdul-Aziz2

Published Online: 26 MAR 2008

DOI: 10.1002/9780470294741.ch16

26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A: Ceramic Engineering and Science Proceedings, Volume 23, Issue 3

26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A: Ceramic Engineering and Science Proceedings, Volume 23, Issue 3

How to Cite

Girgis, M. M., Bhatt, R. T. and Abdul-Aziz, A. (2008) Design Conceptualization of Air-Cooled Coated Silicon Nitride Plates for Gas Turbine Applications, in 26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A: Ceramic Engineering and Science Proceedings, Volume 23, Issue 3 (eds H.-T. Lin and M. Singh), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470294741.ch16

Author Information

  1. 1

    Central State University Manufacturing Engineering Dept. 1400 Brush Row Road Wilberforce, Ohio 45384

  2. 2

    NASA Glenn Research Center 21000 Brookpark Road Cleveland, Ohio 44135

Publication History

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

ISBN Information

Print ISBN: 9780470375785

Online ISBN: 9780470294741

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Keywords:

  • ceramic plate;
  • thermal conductivity;
  • thermal efficiencies;
  • structural ceramics;
  • silicon nitride

Summary

This parametric study investigates the feasibility of cooling of silicon nitride plates with thermal/environmental barrier coatings (TBC/EBC) for high-temperature gas turbine components. Heat transfer analysis coupled with coolant flow analysis, using the ESC task of I-DEAS package, has been conducted for modeling a flat ceramic plate with changing airflow parameters as well as coating configurations. The parametric study was conducted by varying the airflow rate, inlet air temperature, passage surface roughness, and coating configurations including thickness and thermal conductivity. The results include ceramic material and air temperatures, cooling effectiveness, heat transfer coefficient on cooling passage surfaces and heat convected to air. Results with respect to the study key design parameters include variation of ceramic material and air temperatures, cooling effectiveness, heat transfer coefficient on cooling passage surfaces, and heat convected to air. The potential for air-cooled ceramic gas turbine components was demonstrated from the thermal and fluid flow standpoints. Additional work is necessary to further investigate the structural and material aspects for ceramic gas turbine components under engine operating conditions.