公开(公告)号：US12298009B1

公开(公告)日：2025-05-13

申请号：US18677200

申请日：2024-05-29

Applicant: General Electric Company

Inventor： Rachel Yu ,  Nicholas R. Overman ,  William David Magnuszewski

IPC: F23R3/54 ,  F23R3/46 ,  F23R3/58

Abstract: A gas turbine engine including a compressor section for compressing air flowing therethrough to provide a compressed air flow and a reverse flow annular vortex combustor including a combustion chamber having a primary combustion zone, the combustion chamber configured to combust a mixture of a fuel flow and the compressed air flow in the primary combustion zone to generate a primary zone vortex. The reverse flow annular vortex combustor has a combustor liner and one or more driver openings extending through the combustor liner, the one or more driver openings providing a driver air flow formed of the compressed air flow. The driver air flow enters the combustion chamber as a wall of air for shaping and driving the primary zone vortex in the combustion chamber.