A turbine blade assembly (200, 705) for turbo-machines comprising: a blade body (202, 702) 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 (214, 714) at the joint end of the blade body, suitable to abut a disc (216, 716) of a turbo-machine; and a blade root (220, 400, 500, 720) that extends from the blade platform towards the disc, the blade root (220, 400, 500, 720) comprising a plurality of lugs (222a-222d, 722) and a plurality of fillets (224a-224c, 724), wherein the blade root (220, 400, 500, 720) comprises a stress reducing structure (210, 410, 510, 710) capable of countering stress at the plurality of fillets (224, 724), 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 (222a, 222b) of the plurality of lugs (222a-222d), characterized in that the stress reducing structure in the blade root comprises slots (226, 228) with at least one recess, wherein the recess is a break in the continuity of the slots (226, 228), 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 (410, 510) 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 (214, 714) at the joint end of the blade body, suitable to abut a disc (216, 716) of a turbo-machine; and a blade root (220, 400, 500, 720) that extends from the blade platform towards the disc, the blade root (220, 400, 500, 720) comprising a plurality of lugs (222a-222d, 722) and a plurality of fillets (224a-224c, 724), wherein the blade root (220, 400, 500, 720) comprises a stress reducing structure (210, 410, 510, 710) capable of countering stress at the plurality of fillets (224, 724), 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 (222a, 222b) of the plurality of lugs (222a-222d), characterized in that the stress reducing structure in the blade root comprises slots (226, 228) with at least one recess, wherein the recess is a break in the continuity of the slots (226, 228), 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 (410, 510) 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 (222a, 222b) of the plurality of lugs (222a-222d), characterized in that the stress reducing structure in the blade root comprises slots (226, 228) with at least one recess, wherein the recess is a break in the continuity of the slots (226, 228), 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 (410, 510) is capable of expanding azimuthally along a disc circumference of the disc under application of radial strain along a disc radius of the disc.