Patent ID: 8966908
Filing Date: 2015-03-03
Classification: F23C,F23D,F23R

Abstract:
1. A fuel injector for a turbine engine, comprising: a body member disposed about a longitudinal axis; a barrel member located radially outwardly from the body member; an annular passageway extending between the body member and the barrel member from a first end to a second end, the first end configured to be fluidly coupled to a compressor of the turbine engine and the second end configured to be fluidly coupled to a combustor of the turbine engine; a perforated plate, having a plurality of perforations, positioned proximate the first end of the passageway, the perforated plate being configured to direct compressed air into the annular passageway with a first pressure drop; and at least one fuel discharge orifice positioned downstream of the perforated plate, the at least one fuel discharge orifice being configured to discharge a fuel into the annular passageway with a second pressure drop, the second pressure drop having a value between about the first pressure drop and about 1.75 times the first pressure drop.