A turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes are located in an airfoil of the turbine blade according to the coordinates of Table 1.

A turbine vane for a gas turbine engine, including: an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from an inner platform in a radial direction to an outer platform; and wherein the exterior airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in at least one of Tables 1-3, and wherein the set of Cartesian coordinates in Tables 1-3 are offset from a center of an opening located in a forward surface of an attachment lug that extends from a leading edge of the inner platform.

The present application provides a turbine rotor blade including an airfoil shape and a trailing edge shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., inches). The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

In one exemplary embodiment, a blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, an axially forward side and an axially aft side extending radially outward from the gas path surface. A plurality of film cooling holes disposed on at least one of the gas path surface, the first side, the second side, and the aft side, the film cooling holes disposed at locations described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin.

Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.

A turbine blade for a gas turbine engine having an airfoil to platform fillet, wherein the fillet is contoured in accordance with the coordinates of Table 1.

The present application provides a turbine rotor blade including an airfoil shape and a trailing edge shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., inches). The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

A turbine airfoil includes a body that has inner and outer platforms and an airfoil section that extends between the inner and outer platforms. There are film cooling holes that define external breakout points from the body. The external breakout points are located in accordance with Cartesian coordinates of at least points 222 through 256 set forth in Table 1 herein.

A turbine nozzle for a turbine includes: an airfoil having a shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the profile sections at the Z distances are joined smoothly with one another to form the nominal profile. A trailing edge profile for a turbine nozzle is also disclosed.

A turbine nozzle for a gas turbine includes: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs that define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the airfoil profile sections at the Z distances are joined smoothly with one another to form the nominal profile. A trailing edge profile for a turbine nozzle is also disclosed.