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Detailed Cold-Flow Simulation to Estimate Mass Flow Distribution of Aircraft Combustor

[+] Author Affiliations
Mitsumasa Makida, Osamu Nozaki

Japan Aerospace Exploration Agency, Chofu, Tokyo, Japan

Naoki Nakamura

Advanced Science & Intelligence Research Institute, Tokyo, Japan

Paper No. GT2011-46217, pp. 1943-1953; 11 pages
doi:10.1115/GT2011-46217
From:
  • ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition
  • Volume 5: Heat Transfer, Parts A and B
  • Vancouver, British Columbia, Canada, June 6–10, 2011
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5465-5
  • Copyright © 2011 by ASME

abstract

In the TechCLEAN project of JAXA, a combustor for a small aircraft engine has been developed. The combustor was tuned to show the behavior of the Rich-Lean combustion through combustion tests under atmospheric and practical conditions. Finally, the full annular combustor was successfully tuned to reduce NOx emissions to 38.1% of the ICAO CAEP4 standard under ICAO LTO cycles, also sustaining basic performances as an aircraft combustor. In the development process of the combustor, numerical simulation methods were also utilized as analysis tools to accelerate the development of the combustor. To use them in the screening process of the combustor design, we focused on cost-effective simulation methods adopting the cold-flow RANS simulation code UPACS which has been developed in JAXA. Moreover, to simplify the treatment of calculation grids of the combustor with complicated configuration, we also utilized combination of the overset grid method and the attached multi-block grid method. In the previous report, we introduced the overview of the application of the cold-flow simulation in the combustor development process. Subsequently, in this report, we focus on the effect of combustor configuration parameters to the air mass flow ratio among fuel nozzles, dilution air holes and cooling air holes on the combustor linear. Then we also show the estimation method of the effective open area of combustor liners, mass flow ratio between air holes, and total pressure loss of the combustor.

Copyright © 2011 by ASME

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