Turboshaft engine
A turboshaft engine includes a core engine, including a fan section, 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; and a power spool operably coupled to the core engine and configured rotationally drive a fan included within the fan section.
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 high-speed spool, wherein the compressor section includes a high-pressure compressor and the turbine section includes a high-pressure turbine, the high-pressure compressor and the high-pressure turbine being interconnected via the high-speed spool;
a low-speed spool, wherein the compressor section includes a low-pressure compressor and the turbine section includes a low-pressure turbine, the low-pressure compressor and the low-pressure turbine being interconnected via the low-speed spool,
wherein the power spool includes a power turbine positioned downstream of the low-pressure turbine, and
wherein the power spool includes a power shaft configured to interconnect a fan gearbox to the power turbine, the fan gearbox operably connected to the fan;
a supplemental combustor, wherein the supplemental combustor is a rotating detonation combustor, wherein the rotating detonation combustor is positioned within the bypass duct, wherein the rotating detonation combustor includes a fuel-air mixer configured to receive a compressed air and a fuel, wherein the compressed air is received directly via the bypass duct driven by the fan, and wherein the fuel is received from a fuel source via a fuel duct;
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.
2. The gas turbine engine of claim 1 , 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.