Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot.

Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a. characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot.

Abstract: A blade assembly including an outboard blade segment is provided. The outboard blade segment includes an outboard blade shell, first and second outboard bulkheads situated within the outboard blade shell, and an outer box supported by and aligned by the outboard bulkheads. The blade assembly also includes an inboard blade segment including an inboard blade shell, first and second inboard bulkheads situated within the inboard blade shell, and an inner box supported by and aligned by the inboard bulkheads. Further, the inner and the outer boxes are tapered to facilitate insertion of the inner box into the outer box and coupling of the inner and outer boxes.

Abstract: A fan blade including a plurality of fiber composite layers and at least one high elongation fiber composite strip joining one of the fiber composite layers at a joint. A method of making a fan blade includes joining a plurality of fiber composite layers and joining at least one high elongation fiber composite strip to one of the plurality of fiber composite layers. An end of the high elongation fiber composite strip meets an end of the fiber composite layer at a joint.

Abstract: A blade assembly including an outboard blade segment is provided. The outboard blade segment includes an outboard blade shell, first and second outboard bulkheads situated within the outboard blade shell, and an outer box supported by and aligned by the outboard bulkheads. The blade assembly also includes an inboard blade segment including an inboard blade shell, first and second inboard bulkheads situated within the inboard blade shell, and an inner box supported by and aligned by the inboard bulkheads. Further, the inner and the outer boxes are tapered to facilitate insertion of the inner box into the outer box and coupling of the inner and outer boxes.

Abstract: A fan blade including a plurality of fiber composite layers and at least one high elongation fiber composite strip joining one of the fiber composite layers at a joint. A method of making a fan blade includes joining a plurality of fiber composite layers and joining at least one high elongation fiber composite strip to one of the plurality of fiber composite layers. An end of the high elongation fiber composite strip meets an end of the fiber composite layer at a joint.

Abstract: A system and method for analyzing a baseline geometry and, optionally, a modified geometry. The method can include generating a numerical representation of a baseline geometry having baseline elements identified with first identifiers or element identifiers, and then assigning second identifiers or analyzer identifiers to the elements. A selected characteristic of the geometry, such as structural loading, is analyzed with reference to the second or analyzer identifiers. At least one of the elements of the geometry can then be altered in a manner that at least partially automatically adjusts the surrounding geometry, and the same first identifier or element identifier is associated with the altered element as was associated with the baseline, unaltered element. The altered geometry can be analyzed with respect to a third identifier (or another analyzer identifier) and a correspondence between the identifiers, the baseline element, and the altered element can be established and maintained.