US 12,331,702 B2
Turboshaft engine
Steven W. Burd, Cheshire, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Jul. 25, 2024, as Appl. No. 18/784,568.
Application 18/784,568 is a division of application No. 17/734,324, filed on May 2, 2022, granted, now 12,071,912.
Claims priority of provisional application 63/197,072, filed on Jun. 4, 2021.
Prior Publication US 2024/0376851 A1, Nov. 14, 2024
Int. Cl. F02K 3/02 (2006.01); F02C 3/04 (2006.01); F02C 7/36 (2006.01); F02C 9/18 (2006.01)
CPC F02K 3/02 (2013.01) [F02C 3/04 (2013.01); F02C 7/36 (2013.01); F02C 9/18 (2013.01); F05D 2220/32 (2013.01); F05D 2240/35 (2013.01); F05D 2260/606 (2013.01)] 6 Claims
OG exemplary drawing
 
1. A gas turbine engine, comprising:
a core engine, including a compressor section, a primary combustor and a turbine section positioned within a core flow path of the gas turbine engine;
a bypass splitter positioned radially outward of the core engine and configured to house the compressor section, the primary combustor and the turbine section;
a bypass duct positioned radially outward of the bypass splitter;
a power spool operably coupled to the core engine;
a fan section, wherein the power spool is operably connected to a fan within the fan section and configured to rotationally drive the fan;
a supplemental combustor, wherein the supplemental combustor is a rotating detonation combustor that includes a fuel-air mixer configured to receive a compressed air and a fuel, wherein the rotating detonation combustor includes an annular structure positioned downstream of the fuel-air mixer and configured to combust the compressed air and the fuel, wherein the compressed air is provided to the rotating detonation combustor via the bypass duct, and wherein the rotating detonation combustor is positioned within an exit nozzle of the gas turbine engine, the exit nozzle positioned downstream of the bypass duct and wherein the rotating detonation combustor is configured to combust the compressed air, the fuel and an exhaust stream exiting a power turbine;
a bypass flow variable strut configured to manage or regulate a bypass flow through the bypass duct; and
a core flow variable strut configured to at least one of manage or regulate a core flow into a combustion section, wherein both the bypass flow variable strut and the core flow variable strut are positioned aft of the fan and forward of the bypass splitter.