US 12,454,912 B2
Supplemental thrust system for a gas turbine engine
Timothy S. Snyder, Glastonbury, CT (US); and Randolph T. Lyda, Tequesta, FL (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Dec. 3, 2020, as Appl. No. 17/110,619.
Prior Publication US 2022/0178305 A1, Jun. 9, 2022
Int. Cl. F02C 7/00 (2006.01); F02C 7/22 (2006.01)
CPC F02C 7/22 (2013.01) [F05D 2220/32 (2013.01); F05D 2240/35 (2013.01)] 12 Claims
OG exemplary drawing
 
1. An assembly for a turbine engine, comprising:
a compressor section, a combustor section, a turbine section and a flowpath extending sequentially through the compressor section, the combustor section, the turbine section from an airflow inlet to a combustion products exhaust, the combustor section comprising a combustor with a combustion chamber, and a portion of the flowpath that is located downstream of the combustion chamber formed by a flowpath duct;
a fuel injector assembly including a primary duct with an inner flow passage that extends within the primary duct along a centerline of the primary duct, the fuel injector assembly configured to mix fuel with first gas within the inner flow passage to provide a fuel-gas mixture, the fuel injector assembly configured to direct a jet of the fuel-gas mixture into the portion of the flowpath that is located downstream of the combustion chamber, and the inner flow passage discrete from the flowpath; and
a secondary duct extending along a secondary duct centerline, the secondary duct configured to direct second gas into the flowpath about the jet of the fuel-gas mixture, the secondary duct including an outer flow passage that extends circumferentially about the inner flow passage; and
a first protrusion extending from the flowpath duct and projecting axially upstream and radially into the portion of the flowpath that is located downstream of the combustion chamber towards the centerline of the flowpath duct;
the combustor located radially outboard of and axially overlapping the fuel injector assembly and the portion of the flowpath that is located downstream of the combustion chamber;
the fuel injector assembly configured to bleed the first gas from the combustion chamber, the fuel injector assembly configured to direct the jet of the fuel-gas mixture into the portion of the flowpath that is located downstream of the combustion chamber at a first location that is circumferentially aligned with and downstream of the first protrusion; and
the centerline of the primary duct angularly offset from a centerline of the flowpath duct by an acute angle, and the centerline of the primary duct extending from the combustion chamber towards a forward end of the assembly;
the secondary duct centerline angularly offset from the centerline of the flowpath duct by an acute angle.