System for an inlet guide vane shroud and baffle assembly

An inlet guide vane (IGV) assembly for a gas turbine engine, the gas turbine engine including a central axis, a fan assembly positioned at a forward end, and an exhaust outlet positioned at an aft end, said IGV assembly comprising:

• a shroud comprising a first end configured to couple to an annular support member of the gas turbine engine, a second end, a distal end comprising an axially aft extending lip, said distal end further comprising a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine, said shroud further comprising an arcuate shroud body extending between said distal end and said second end, wherein said shroud extends circumferentially about the central axis;
• and
• a baffle coupled to an aft side of said shroud, said baffle comprising a radially outward end coupled to said aft side, a radially inward end coupled to said axially aft extending lip, and an arcuate baffle body extending therebetween, wherein said baffle extends circumferentially about the central axis;
• and
• a plurality of IGVs separate from the annular support member, each IGV of said plurality of IGVs coupled to a radially outward surface of said shroud aft of the first end, wherein said radially outward surface is configured to engage at least one IGV of said plurality of IGVs thereto, wherein said plurality of IGVs are arranged radially about the central axis.

A gas turbine engine including a central axis, a fan assembly positioned at a forward end, and an exhaust outlet positioned at an aft end, said gas turbine comprising:

• a core engine comprising a compressor, a combustor, and a turbine coupled in a serial flow relationship;
• a power engine comprising a fan and a power turbine coupled together on a common shaft, said power engine coaxial with said core engine;
• a shroud and baffle assembly comprising:
• a shroud comprising a first end configured to couple to an annular support member of the gas turbine engine, a second end, a distal end comprising an axially aft extending lip, wherein said axially aft extending lip comprises a plurality of scallops, each scallop of said plurality of scallops comprising a cut away extending into at least a portion of said axially aft extending lip, said distal end further comprising a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of said gas turbine engine, said shroud further comprising an arcuate shroud body extending between said distal end and said second end;
• and
• a baffle coupled to an aft side of said shroud, said baffle comprising a radially outward end coupled to said aft side, a radially inward end coupled to said axially aft extending lip, and an arcuate baffle body extending therebetween, said baffle extending aftward into an annular space of said gas turbine engine;
• and
• a plurality of inlet guide vanes (IGVs), each IGV of said plurality of IGVs coupled radially to and between a radially outward surface of said shroud and a radially inward surface of an annular housing of said compressor, wherein said shroud, said baffle, said plurality of IGVs, and said annular housing are arranged circumferentially about the central axis.