A turbine blade assembly for turbo-machines comprising: a blade body including a free end and a joint end , the blade body comprising: an airfoil section along at least one side of the blade body extending from the joint end to the free end; and a blade platform at the joint end of the blade body , suitable to abut a disc of a turbo-machine; and a blade root that extends from the blade platform towards the disc, the blade root comprising a plurality of lugs (222a-222d, 722) and a plurality of fillets (224a-224c, 724), wherein the blade root comprises a stress reducing structure capable of countering stress at the plurality of fillets , wherein the blade root further comprises: a central root section along central longitudinal axis of the blade root ; wherein the stress reducing structure is located in the central root section between at least two lugs of the plurality of lugs (222a-222d), characterized in that the stress reducing structure in the blade root comprises slots with at least one recess , wherein the recess is a break in the continuity of the slots , and at least one a compression structure at the at least one recess , wherein the compression structure is capable of generating compressive action along the disc radius to counter the stress at the plurality of fillets (224a-224c, 724), wherein the stress reducing structure is capable of expanding azimuthally along a disc circumference of the disc under application of radial strain along a disc radius of the disc. an airfoil section along at least one side of the blade body extending from the joint end to the free end; and a blade platform at the joint end of the blade body , suitable to abut a disc of a turbo-machine; and a blade root that extends from the blade platform towards the disc, the blade root comprising a plurality of lugs (222a-222d, 722) and a plurality of fillets (224a-224c, 724), wherein the blade root comprises a stress reducing structure capable of countering stress at the plurality of fillets , wherein the blade root further comprises: a central root section along central longitudinal axis of the blade root ; wherein the stress reducing structure is located in the central root section between at least two lugs of the plurality of lugs (222a-222d), characterized in that the stress reducing structure in the blade root comprises slots with at least one recess , wherein the recess is a break in the continuity of the slots , and at least one a compression structure at the at least one recess , wherein the compression structure is capable of generating compressive action along the disc radius to counter the stress at the plurality of fillets (224a-224c, 724), wherein the stress reducing structure is capable of expanding azimuthally along a disc circumference of the disc under application of radial strain along a disc radius of the disc. a central root section along central longitudinal axis of the blade root ; wherein the stress reducing structure is located in the central root section between at least two lugs of the plurality of lugs (222a-222d), characterized in that the stress reducing structure in the blade root comprises slots with at least one recess , wherein the recess is a break in the continuity of the slots , and at least one a compression structure at the at least one recess , wherein the compression structure is capable of generating compressive action along the disc radius to counter the stress at the plurality of fillets (224a-224c, 724), wherein the stress reducing structure is capable of expanding azimuthally along a disc circumference of the disc under application of radial strain along a disc radius of the disc. <EOS>