Abstract: A gas turbine blade for a gas turbine engine includes an attachment, a blade neck portion, a platform, an airfoil, and a shroud. The gas turbine engine has an operating speed range. The blade neck portion extends radially outward from the attachment. The platform is attached to the blade neck portion opposite the attachment. The airfoil extends radially outward from the platform. The airfoil includes a leading edge, a trailing edge, and an axial chord defined between the leading and trailing edges. The axial chord defines a mid-chord point. The shroud is attached to an end of the airfoil. The shroud includes an upper surface and a modal response tuning component attached to the upper surface of the shroud. The modal response tuning component is offset from the mid-chord point a predetermined distance to move modal response of the gas turbine blade outside of the operating speed range.

Abstract: An airfoil for a gas turbine engine, the airfoil comprising a wall having a first surface, a second surface, and a passageway extending through the wall from a first opening in the first surface to a second opening in the second surface, the passageway having one or more sections between the first opening and the second opening, the one or more sections in fluid communication with each other, the plurality of sections comprising a first diffuser section providing a first change in cross-sectional area within the passageway, a second diffuser section providing a second change in cross-sectional area within the passageway, a flow conditioning section, and an edge section having two surfaces set opposite each other across the passageway, the two surfaces extending along the passageway substantially in parallel to one another, the edge section being located adjacent to the second opening.

Abstract: An apparatus for providing improved cooling to a combustion liner of a gas turbine combustor is provided. A plurality of flow deflectors is secured to a flow sleeve in order to improve the flow of impingement air from a flow sleeve to the combustion liner outer surface, such that the amount of impingement air being swept away by a cross flow of cooling air is reduced.

Abstract: An airfoil for a gas turbine engine, the airfoil comprising a wall having a first surface, a second surface, and a passageway extending through the wall from a first opening in the first surface to a second opening in the second surface, the passageway having one or more sections between the first opening and the second opening, the one or more sections in fluid communication with each other, the plurality of sections comprising a first diffuser section providing a first change in cross-sectional area within the passageway, a second diffuser section providing a second change in cross-sectional area within the passageway, a flow conditioning section, and an edge section having two surfaces set opposite each other across the passageway, the two surfaces extending along the passageway substantially in parallel to one another, the edge section being located adjacent to the second opening.

Abstract: An apparatus for providing improved cooling to a combustion liner of a gas turbine combustor is provided. A plurality of flow deflectors is secured to a flow sleeve in order to improve the flow of impingement air from a flow sleeve to the combustion liner outer surface, such that the amount of impingement air being swept away by a cross flow of cooling air is reduced.

Abstract: A system and method for securing a blade within a disk so as to eliminate the need for permanently deforming materials associated with the blade disk is disclosed. A recess is formed generally within each slot used to secure a blade within the disk. A retaining insert is positioned within the recess and a wedge insert is positioned within a slot of the retaining insert, such that a pressure is applied to the retaining insert thereby deflecting the retaining insert into a pre-set radial position to prevent axial movement of the blade within the slot of the disk.

Abstract: A system and method for securing a blade within a disk so as to eliminate the need for permanently deforming materials associated with the blade disk is disclosed. A recess is formed generally within each slot used to secure a blade within the disk. A retaining insert is positioned within the recess and a wedge insert is positioned within a slot of the retaining insert, such that a pressure is applied to the retaining insert thereby deflecting the retaining insert into a pre-set radial position to prevent axial movement of the blade within the slot of the disk.