Gas turbine engine having a thrust reverser system with drag link connectors at inter-compressor frame structure

A gas turbine engine comprising:

• a fan assembly;
• a turbo-engine arranged to drive the fan assembly, the turbo-engine at least partially encased within a turbo-engine cowl structure;
• a nacelle surrounding the fan assembly and at least a portion of the turbo-engine, a fan bypass airflow passage being arranged between the nacelle and the turbo-engine cowl structure;
• and
• a thrust reverser system arranged, at least in part, in the nacelle and including a plurality of actuators, a plurality of thrust reverser blocking doors, and a plurality of drag links connected with respective ones of the plurality of thrust reverser blocking doors and with the turbo-engine cowl structure via a plurality of thrust reverser drag link connectors,
• wherein the turbo-engine includes (a) a low-pressure compressor, (b) a high-pressure compressor arranged downstream of the low-pressure compressor, (c) an inter-compressor frame structure arranged between the low-pressure compressor and the high-pressure compressor, the inter-compressor frame structure including an outer frame portion having a cowl door engagement member arranged on an upstream side of the outer frame portion, and (d) a plurality of cowl doors defining at least a portion of the turbo-engine cowl structure, each cowl door among the plurality of cowl doors includes (i) an inter-compressor frame engagement portion arranged to engage with the cowl door engagement member of the inter-compressor frame structure, and (ii) the plurality of thrust reverser drag link connectors arranged on an outer side of the cowl door and arranged between the upstream side of the inter-compressor frame structure and a downstream side of the inter-compressor frame structure.