Abstract: Systems provide enhanced cooling of tip regions of turbine blades. A cooling system includes a turbine blade with a root, a base, a tip, a leading edge, a trailing edge, an outer structure that includes a pressure side wall, a suction side wall and a tip cap at its tip. A core in the blade defines a leading channel that ejects cooling air through the leading edge. A primary tip flag channel ejects cooling air through the tip and the trailing edge. A secondary tip flag channel ejects cooling air through the trailing edge. The primary tip flag channel and the secondary tip flag channel promote cooling of the tip due to the locations in the tip area and their delivery of low temperature and high pressure cooling air thereto.

Abstract: A turbine vane airfoil and a turbine nozzle that includes the turbine vane airfoil. The turbine vane airfoil includes an airfoil defining a chamber proximate a surface, and an impingement tube. The impingement tube includes a first wall and a second wall. The first wall defines a plurality of first apertures, and each has a first upstream surface portion opposite a first downstream surface portion. The second wall defines a plurality of second apertures, and each has a second upstream surface portion opposite a second downstream surface portion. Each of the first apertures cooperate with a respective one of the second apertures to direct a cooling fluid onto the surface, and the first downstream surface portion of at least one of the first apertures includes a first point that is collinear with a second point of the second downstream surface portion of the respective one of the second apertures.

Abstract: A turbine component includes a hot wall, a cold wall spaced apart from the hot wall and a conduit defined between the hot wall and the cold wall. A cooling system is defined in the conduit. The cooling system includes a plurality of cooling pins, each including a first end having a first cross-sectional area and a second end having a second cross-sectional area. Each cooling pin includes a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end. The pin leading edge is defined by a first diameter and a pin trailing edge is defined by a second diameter. At least one first cooling pin has the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

Abstract: A turbine component includes a hot wall, a cold wall spaced apart from the hot wall and a conduit defined between the hot wall and the cold wall. A cooling system is defined in the conduit. The cooling system includes a plurality of cooling pins, each including a first end having a first cross-sectional area and a second end having a second cross-sectional area. Each cooling pin includes a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end. The pin leading edge is defined by a first diameter and a pin trailing edge is defined by a second diameter. At least one first cooling pin has the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body. At least one of the cooling holes has cross-sectional shape with a first concave portion and a first convex portion.

Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body. At least one of the cooling holes has cross-sectional shape with a first concave portion and a first convex portion.