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