US 12,298,009 B1
Turbine engine having a reverse flow annular vortex combustor
Rachel Yu, Medford, MA (US); Nicholas R. Overman, Sharonville, OH (US); and William David Magnuszewski, Cincinnati, OH (US)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 29, 2024, as Appl. No. 18/677,200.
Int. Cl. F23R 3/54 (2006.01); F23R 3/46 (2006.01); F23R 3/58 (2006.01)
CPC F23R 3/54 (2013.01) [F23R 3/46 (2013.01); F23R 3/58 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
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 including:
a combustor liner; and
one or more driver openings extending radially through the combustor liner, the one or more driver openings providing a driver air flow formed of the compressed air flow, wherein 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, wherein one or more of the one or more driver openings are oriented at an angle in a downstream direction to direct the driver air flow in the downstream direction to pull combustion gases from the primary zone vortex downstream within the combustion chamber.