Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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).

Abstract: 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.

Abstract: 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.

Abstract: A thyroplasty implant having a tiered base for anchoring in a window cut through a thyroid lamina and a projecting member for causing medial displacement of a vocal cord. The tiered base has a bottom tier, a middle tier, and an upper tier, the bottom tier and upper tier being larger in area than the middle tier so as to facilitate anchoring the base in the window. The base is made of a firm biocompatible material to facilitate firm anchoring of the implant, and the projecting member being made of softer, biocompatible material that is sufficiently soft to avoid damage to the vocal cord. The projecting member is generally triangular in shape and has a portion that extends in a posterior direction from the base. A measuring tool having a projecting member of similar shape to that of the implant and a movable stop member is used to measure the optimum size implant.

Abstract: A thyroplasty implant having a tiered base for anchoring in a window cut through a thyroid lamina and a projecting member for causing medial displacement of a vocal cord. The tiered base has a bottom tier, a middle tier, and an upper tier, the bottom tier and upper tier being larger in area than the middle tier so as to facilitate anchoring the base in the window. The base is made of a firm biocompatible material to facilitate firm anchoring of the implant, and the projecting member being made of softer, biocompatible material that is sufficiently soft to avoid damage to the vocal cord. The projecting member is generally triangular in shape and has a portion that extends in a posterior direction from the base. A measuring tool having a projecting member of similar shape to that of the implant and a movable stop member is used to measure the optimum size implant.

Abstract: A tool for measuring a tracheotomy stoma for proper fitting of a tracheotomy tube including an integral member having a plurality of legs and a shaft that extend from it, each leg having a free end and a base end secured to other legs, each leg being sufficiently long to extend from the outside of a patient's skin to inside the tracheal passage, each leg being spaced from other legs by at least about 90.degree.