公开(公告)号：US20170184309A1

公开(公告)日：2017-06-29

申请号：US15392749

申请日：2016-12-28

Applicant: GE AVIO S.r.l.

Inventor： Fabio TURRINI ,  Antonio PESCHIULLI ,  Marco MOTTA

IPC: F23R3/28 ,  F23R3/10 ,  F02C7/22

CPC classification number: F23R3/286 ,  F02C7/222 ,  F05D2220/32 ,  F05D2240/35 ,  F23D2900/11101 ,  F23R3/10

Abstract: An injection assembly for a combustor of a gas turbine has an outer body provided with inlet passages for comburent air, a conical tubular portion housed inside the outer body and delimiting partly an inner duct and an outer annular duct; a first and a second supply means for supplying a liquid fuel into the inner duct and, respectively, into the outer annular duct; at least one circumferential annular seat formed being carried by one of the tubular portion and the outer body, so as to collect a mass of liquid fuel advancing in the outer annular duct and make uniform the flow of liquid flowing out of the circumferential annular seat.