Tandem rotor blades

A gas turbine engine, comprising:

• a compressor section including a low pressure compressor (LPC) and a high pressure compressor (HPC), wherein the HPC is aft of the LPC, and wherein the compressor section includes a compressor case defining a centerline axis, and a rotor disk defined between the compressor case and the centerline axis;
• and
• a plurality of stages defined radially inward relative to the compressor case, wherein the plurality of stages includes at least one tandem blade stage, wherein the at least one tandem blade stage includes:
• a plurality of blade pairs, each blade pair being circumferentially spaced apart from the other blade pairs, each blade pair being operatively connected to the rotor disk, wherein each blade pair includes a forward blade and an aft blade, wherein the aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.