Gas turbine engine with variable compressor inlet

A gas turbine engine, comprising:

• a fan section;
• a fan bypass air path;
• a compressor section;
• a combustion section;
• a turbine section;
• an annular compressor inlet;
• inlet guide vanes;
• and
• an inlet panel structure actuation system;
• wherein the annular compressor inlet is defined by an inner radial surface and a plurality of inlet panel structures, wherein each inlet panel structure includes an inlet side segment and a bypass side segment, and the inlet side segments collectively define an outer radial surface of the compressor inlet;
• wherein the inlet side segment and the bypass side segment of each inlet panel structure intersect at an inlet panel leading edge;
• wherein the inlet panel structures are disposable in a radial inner most configuration and in a radial outer most configuration, wherein in the radial inner most configuration, the inlet panel leading edge is disposed a first distance from the inner radial surface, and wherein in the radial outer most configuration, the inlet panel leading edge is disposed a second distance from the inner radial surface, and wherein the second distance is greater than the first distance;
• wherein the inlet guide vanes are disposed radially across the annular compressor inlet at the plurality of inlet panel structures;
• wherein the inner radial surface is defined by an inner radial platform of the inlet guide vanes;
• and
• wherein the inlet panel structure actuation system is configured to selectively actuate the inlet panel structures between the radial inner most configuration and the radial outer most configuration and to translate the inlet panel leading edge of each inlet panel structure radially relative to the inlet guide vanes.