公开(公告)号：US20240392967A1

公开(公告)日：2024-11-28

申请号：US18652159

申请日：2024-05-01

Applicant: ROLLS-ROYCE plc

Inventor： Karpaga Vipran KANNAN ,  Joseph R. HARDY ,  Ryan L. ROGERS ,  Andrés E. LEIVA GONZALEZ ,  Shahrokh SHAHPAR

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/34

Abstract: A fuel swirl nozzle for a gas turbine engine comprises, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion. An inlet to the fuel stem portion is fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion is fluidly sealed against the fuel/air swirler portion. The fuel/air swirler portion has a cross-sectional profile that is generally dolioform shaped along an axis parallel to the engine's longitudinal axis, and has a first end and a second end. The first end of the fuel/air swirler portion has an air inlet face, and the second end of the fuel/air swirler portion has a fuel/air mixture outlet face. The first end comprises a rim portion enclosing the air inlet face in which the rim portion has a rim portion radius (rrim) normal to an outer circumference of the inlet face.