United Technologies Corporation

Richard J Pawlaczyk

Paul W Duesler

Matthew D Nicolson

C Vincent Loffredo

Norman Pietruska

John W Magowan

Gilbert B Wilcox

Annette M Pighetti

Richard A Schwarz, Jr

Jon G Rowe

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.

Method of forming a windage cover for a gas turbine engine the method including forming a continuous ring from a sheet of metal and bending and cutting the continuous ring to form at least two arcuate segments

Stator assembly for a rotary machine

A method for refurbishing or restoring a turbine vane or other airfoil to restore a desired flow area includes the steps of: providing a plate to be used to restore the flow area on the airfoil; cutting the plate into a desired shape; machining a series of tapers into the cut plate so that the cut plate has a single region with a substantially uniform thickness; overlaying a surface of the airfoil with the pre-cut, pre-shaped plate so that the substantially uniform thickness region is positioned over that part of the airfoil where the flow area is to be restored; and attaching the pre-cut, pre-shaped plate to the airfoil. The refurbishment or restoration method further includes heat treating the pre-cut, pre-shaped plate so that the plate softens and conforms to the shape of the airfoil surface.

Turbine vane flow area restoration method

A turbine vane for a gas turbine engine core adaptable to be operated in a variety of thrust regimes is disclosed. Various construction details are developed which provide cooling to an inner platform of the turbine vane. In one particular embodiment, a turbine vane includes a hollow core permitting cooling fluid to pass through the vane and an inner platform having a pocket disposed therein, the pocket being in fluid communication with the core. Heat is exchanged between the platform and the cooling fluid within the pocket. Cooling holes extend between the pocket and a flow surface of a platform to provide cooling of the flow surface.

Turbine vane having dedicated inner platform cooling

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Southington, CT, United States of America

Richard J Pawlaczyk