公开(公告)号：US20190056108A1

公开(公告)日：2019-02-21

申请号：US15681851

申请日：2017-08-21

Applicant: General Electric Company

Inventor： Hejie Li ,  David Louis Burrus ,  Arvind Kumar Rao ,  Sreejith Keloth

IPC: F23R3/06

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a fuel nozzle and an annular shroud. The fuel nozzle comprises a centerbody extended along a lengthwise direction. The fuel nozzle defines a nozzle centerline extended through the centerbody of the fuel nozzle along the lengthwise direction. The fuel nozzle defines a plurality of exit openings in circumferential arrangement on the centerbody relative to the nozzle centerline. The annular shroud surrounds the centerbody of the fuel nozzle. At least a portion of the shroud defines a contoured structure defining a waveform.