United Technologies Corporation

Raytheon Technologies Corporation

Stuart K Montgomery

Yehia M El-Aini

Robert J Morris

Ron I Prihar

Gary Alan Davis

William D Owen

Lawrence P Roberts

Joshua L Mardis

William S Mitchell

John Johnsen

A process for repairing an aircraft engine component includes receiving a plurality of component measurements of a damaged component, comparing the plurality of component measurements of the damaged component to a finite element model of an ideal component, generating a finite element model of the damaged component based at least partially on the comparison, determining a corrective material removal operation based at least in part on the finite element model of the damaged component, and removing material from the damaged component according to the corrective material removal operation, thereby creating a repaired component.

Process for repairing turbine engine components

A split case compressor including a first compressor case segment including a first split flange extending axially and a first axial flange extending circumferentially about the first compressor case segment. The compressor also includes a second compressor case segment including a second split flange extending axially and a second axial flange extending circumferentially about the second compressor case segment, the first and second split flanges forming an overall split flange for securing the first compressor case segment and the second compressor case segment to each other. The compressor further includes a notch of at least one of the first axial flange and the second axial flange proximate the overall split flange.

Notched axial flange for a split case compressor

A turbine disk includes a rotor and a plurality of turbine blades, each comprising a root at a proximal end secured to the rotor and a tip having a shroud at a distal end. The shroud includes a inner diameter surface, an outer diameter surface and a segmented sidewall surface separating the inner and outer diameter surfaces. The shrouds of adjacent turbine blades are separated by a tip shroud damper, and which includes a retention rail that cooperates with the outer diameter surface to maintain a positional relationship of the damper, a inner flange that engages the segmented sidewall surface, and a web that separates the retention rail and the inner flange. The tip shroud damper reduces the vibratory responses of modes involving axial and radial shroud motion to prevent high cycle fatigue (HCT).

Airfoil tip shroud damper

A stationary labyrinth seal system includes a seal housing having an annular cavity, a plurality of damping devices, and a retaining ring. The damping devices are positioned within the annular cavity and are maintained within the annular cavity by the retaining ring.

Damping device for a stationary labyrinth seal

Growing community of inventors

Jupiter, FL, United States of America

Stuart K Montgomery