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

Defence Science Journal

S.N. Singh¹  D.P. Agrawal¹  Sanjeev Bharani¹ 

[1] Indian Institute of Technology, New Delhi

关键词: Flow distribution;    Reverse flow gas turbine combustor;    Inlet flow velocity.;   

DOI  :  

学科分类：社会科学、人文和艺术（综合）

来源: Defence Scientific Information & Documentation Centre

【 摘 要 】

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.

【 授权许可】

Unknown