Abstract: A stator assembly having a windage cover for structure adjacent to a cavity bounded by rotating elements in a rotary machine is disclosed. Various construction details are developed for damping vibrations in the windage cover as the windage cover bounds a cavity having swirling high velocity gases that are capable of transmitting acoustic energy and kinetic energy to adjacent structure. In one detailed embodiment, the windage cover in the uninstalled condition has diverging arms that are resiliently compressed during installation to exert a frictional force on the adjacent structure.

Abstract: An example finishing tool form assembly includes a base and a superabrasive bonded to a surface of the base. The superabrasive is configured to be reciprocated with the base relative to a longitudinally extending recess of a component to finish at least one surface of the component.

Abstract: A stator assembly having a windage cover for structure adjacent to a cavity bounded by rotating elements in a rotary machine is disclosed. Various construction details are developed for damping vibrations in the windage cover as the windage cover bounds a cavity having swirling high velocity gases that are capable of transmitting acoustic energy and kinetic energy to adjacent structure. In one detailed embodiment, the windage cover in the uninstalled condition has diverging arms that are resiliently compressed during installation to exert a frictional force on the adjacent structure.

Abstract: A stator assembly having a windage cover for structure adjacent to a cavity bounded by rotating elements in a rotary machine is disclosed. Various construction details are developed for damping vibrations in the windage cover as the windage cover bounds a cavity having swirling high velocity gases that are capable of transmitting acoustic energy and kinetic energy to adjacent structure. In one detailed embodiment, the windage cover in the uninstalled condition has diverging arms that are resiliently compressed during installation to exert a frictional force on the adjacent structure.

Abstract: A stator assembly having a windage cover for structure adjacent to a cavity bounded by rotating elements in a rotary machine is disclosed. Various construction details are developed for damping vibrations in the windage cover as the windage cover bounds a cavity having swirling high velocity gases that are capable of transmitting acoustic energy and kinetic energy to adjacent structure. In one detailed embodiment, the windage cover in the uninstalled condition has diverging arms that are resiliently compressed during installation to exert a frictional force on the adjacent structure.

Abstract: The present invention relates to a bleed system for use in a gas turbine engine. The bleed system comprises a plurality of blades with each of the blades having an airfoil member and a platform structure. The bleed system further has at least one interblade passage formed by adjacent ones of the airfoil members and an inner endwall formed by the platform structures. A bleed hole is located in the at least one interblade passage for extracting a portion of a fluid passing therethrough. The bleed positioning within the stator passage, both axially and circumferentially, is selected for optimum balance of static pressure and tangential velocity.

Abstract: The present invention relates to a bleed system for use in a gas turbine engine. The bleed system comprises a plurality of blades with each of the blades having an airfoil member and a platform structure. The bleed system further has at least one interblade passage formed by adjacent ones of the airfoil members and an inner endwall formed by the platform structures. A bleed hole is located in the at least one interblade passage for extracting a portion of a fluid passing therethrough. The bleed positioning within the stator passage, both axially and circumferentially, is selected for optimum balance of static pressure and tangential velocity.

Abstract: With a turbo machine comprises a trunnion portion and an airfoil portion, the airfoil portion is defined by a leading edge, a trailing edge, and a pair of side edges. One or more of the side edges comprises a fin which extends from proximate to the trunnion portion toward the trailing edge of the airfoil portion. The fin tapers in thickness from the trunnion portion to the trailing edge portion. The fin may extend above and/or below the top and bottom surfaces of the airfoil. The fin may be formed on a portion of one or both of the side edges.