Propulsion system with adjustable core inlet guide vane

An assembly for an aircraft, comprising:

• a compressor section;
• a combustor section;
• a turbine section;
• a flowpath extending longitudinally through the compressor section, the combustor section and the turbine section from a flowpath inlet to a flowpath exhaust;
• a first stator vane structure comprising a plurality of first stator vanes arranged in an annular array, each of the plurality of first stator vanes extending across the flowpath, and the plurality of first stator vanes comprising a first stator vane with at least one of an adjustable first stator vane pitch or an adjustable first stator vane camber;
• and
• a second stator vane structure arranged longitudinally along the flowpath between the first stator vane structure and an upstream-most stage of compressor blades in the compressor section, the second stator vane structure comprising a plurality of second stator vanes arranged in an annular array, and each of the plurality of second stator vanes extending across the flowpath.

An assembly for an aircraft, comprising:

• a compressor section;
• a combustor section;
• a turbine section;
• a flowpath extending longitudinally through the compressor section, the combustor section and the turbine section from a flowpath inlet to a flowpath exhaust;
• an inlet vane structure comprising a plurality of inlet guide vanes arranged in an annular array, each of the plurality of inlet guide vanes extending across the flowpath, the plurality of inlet guide vanes comprising a first inlet guide vane spaced a distance from the flowpath inlet longitudinally along the flowpath, the first inlet guide vane having a vane dimension, and the distance equal to or less than five times the vane dimension;
• and
• an inlet vane actuation system configured to change at least a parameter of the first inlet guide vane.