Abstract: A rotor blade may include a tip shroud having at least one seal tooth disposed at an angle that may be relative to the engine centerline when in an assembled condition, the leading edge of the tip shroud and/or the trailing edge of the tip shroud.

Abstract: A turbine for a gas turbine engine including a turbine nozzle assembly that facilitates reducing an operating temperature of rotor blades in a cost-effective and reliable manner is described. Each rotor blade includes a tip that rotates in close proximity to a shroud that extends circumferentially around the rotor assembly. The turbine nozzle assembly includes a plurality of turbine vane segments that channel combustion gases to downstream rotor blades. Each turbine vane segment extends radially outward from an inner platform and includes a tip, a root, and a body that extends therebetween. The turbine vane segment tip is formed integrally with an outer band that mounts the vane segments within the gas turbine engine. The outer band is in flow communication with a cooling fluid source, and includes at least one opening.

Abstract: An airfoil for use in a gas turbine engine. The airfoil includes a body having an interior surface defining a hollow cavity in the airfoil having an inlet and an outlet. The airfoil also includes a partition within the cavity dividing the cavity into a first cooling passage and a second cooling passage. The first cooling passage communicates with the inlet for delivering cooling air to the first passage and the second cooling passage communicates with the outlet for exhausting cooling air from the second passage. The partition has a cooling hole therein extending between the first passage and the second passage permitting cooling air to pass from the first passage to the second passage. The cooling hole is sized and positioned with respect to the interior surface of the airfoil for directing cooling air toward a portion of the interior surface of the airfoil so the cooling air impinges upon the portion.

Abstract: A turbine for a gas turbine engine including a turbine nozzle assembly that facilitates reducing an operating temperature of rotor blades in a cost-effective and reliable manner is described. Each rotor blade includes a tip that rotates in close proximity to a shroud that extends circumferentially around the rotor assembly. The turbine nozzle assembly includes a plurality of turbine vane segments that channel combustion gases to downstream rotor blades. Each turbine vane segment extends radially outward from an inner platform and includes a tip, a root, and a body that extends therebetween. The turbine vane segment tip is formed integrally with an outer band that mounts the vane segments within the gas turbine engine. The outer band is in flow communication with a cooling fluid source, and includes at least one opening.