Blade assembly for gas turbine engine

A blade assembly for a gas turbine engine, the blade assembly comprising:

• a rotor comprising a rotor blade and a rotor disc defining a bucket groove at least partially receiving the rotor blade therein, wherein the bucket groove receives a cooling fluid from a first cavity upstream of the rotor;
• a stator disposed downstream of the rotor, wherein the stator and the rotor define a second cavity therebetween downstream of the first cavity;
• a seal plate coupled to the rotor and facing the first cavity, wherein the seal plate defines an aperture therethrough in fluid communication with the bucket groove;
• and
• a sealing member comprising a control arm extending at least radially towards the rotor, wherein the sealing member and the rotor define a flow cavity therebetween in fluid communication with the aperture of the seal plate, and wherein the control arm and the seal plate define a gap therebetween fluidly communicating the flow cavity with the second cavity;
• wherein the flow cavity receives the cooling fluid flowing through the bucket groove of the rotor disc and the aperture of the seal plate, wherein the control arm deflects at least a portion of the cooling fluid entering the flow cavity, and wherein the gap allows at least a portion of the cooling fluid to exit the flow cavity and enter the second cavity.