Velocity Distribution in the Annuli of a Plane Reverse-Flow Combustor Model

  • Sanjeev Bharani Indian Institute of Technology, New Delhi
  • S.N. Singh Indian Institute of Technology, New Delhi
  • D.P. Agrawal Indian Institute of Technology, New Delhi
Keywords: Flow distribution, Reverse flow gas turbine combustor, Inlet flow velocity.

Abstract

This paper reports the yclodity profiles and flow distribution in the annuli of a plane reverse-flow gas turbine GOmbustor model. Based on these, flow-split through different liner holes and swirlers has been estimated. it is seen that percentage flow-split through the outer liner surface holes, compared to that through liner dome and inner liner surface holes, is not affected  significantly by increase in theinlet flow velocity.

Author Biographies

Sanjeev Bharani, Indian Institute of Technology, New Delhi
Indian Institute of Technology, New Delhi
S.N. Singh, Indian Institute of Technology, New Delhi
Indian Institute of Technology, New Delhi
D.P. Agrawal, Indian Institute of Technology, New Delhi
Indian Institute of Technology, New Delhi

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Published
2013-01-01
How to Cite
Bharani, S., Singh, S., & Agrawal, D. (2013). Velocity Distribution in the Annuli of a Plane Reverse-Flow Combustor Model. Defence Science Journal, 50(2), 137-145. https://doi.org/10.14429/dsj.50.3368
Section
Aeronautical Systems