A blade for a turbine engine comprising: a generally elongated airfoil comprising a leading edge, a trailing edge connecting a pressure side and a suction side, a radially outer tip cap having a tip cap upper surface at a blade tip of the airfoil, a root coupled to the elongated airfoil generally opposite the blade tip supporting the blade and for coupling the blade to a disc, and an internal cooling system formed from at least one cavity positioned within the generally elongated airfoil; a squealer tip extending radially outward from the tip cap upper surface comprising at least a first tip cap rib and a second tip cap rib; and at least one densified oxide dispersion strengthened layer deposited on and extending radially outward from the tip cap upper surface, wherein the densified oxide dispersion strengthened layer, ODS, is defined by an elongated grain structure and dispersion of oxide and other particles, the blade further comprising an acute angled ledge that extends out from along the pressure side of the airfoil, wherein the acute angle is from an extended plane of the majority of the pressure side and opening outward from the pressure side, wherein the acute angled ledge comprises a top portion and a lower portion, wherein the bottom portion extends out from the pressure side and the top portion further extends the ledge to an approximately equal radial height as the blade tip, wherein the tip cap comprises at least one film cooling hole, positioned in between the first tip cap rib and an edge along the pressure side of the airfoil with an exhaust outlet of the at least one film cooling hole in the tip cap upper surface and an inlet, that couples the at least one film cooling hole with the at least one cavity forming the internal cooling system, and wherein the at least one film cooling hole is positioned through the acute angled ledge exiting in the tip cap upper surface of the airfoil. a generally elongated airfoil comprising a leading edge, a trailing edge connecting a pressure side and a suction side, a radially outer tip cap having a tip cap upper surface at a blade tip of the airfoil, a root coupled to the elongated airfoil generally opposite the blade tip supporting the blade and for coupling the blade to a disc, and an internal cooling system formed from at least one cavity positioned within the generally elongated airfoil; a squealer tip extending radially outward from the tip cap upper surface comprising at least a first tip cap rib and a second tip cap rib; and at least one densified oxide dispersion strengthened layer deposited on and extending radially outward from the tip cap upper surface, wherein the densified oxide dispersion strengthened layer, ODS, is defined by an elongated grain structure and dispersion of oxide and other particles, the blade further comprising an acute angled ledge that extends out from along the pressure side of the airfoil, wherein the acute angle is from an extended plane of the majority of the pressure side and opening outward from the pressure side, wherein the acute angled ledge comprises a top portion and a lower portion, wherein the bottom portion extends out from the pressure side and the top portion further extends the ledge to an approximately equal radial height as the blade tip, wherein the tip cap comprises at least one film cooling hole, positioned in between the first tip cap rib and an edge along the pressure side of the airfoil with an exhaust outlet of the at least one film cooling hole in the tip cap upper surface and an inlet, that couples the at least one film cooling hole with the at least one cavity forming the internal cooling system, and wherein the at least one film cooling hole is positioned through the acute angled ledge exiting in the tip cap upper surface of the airfoil.