Abstract: A flow mixing lobe for an exhaust diffuser includes a first flange member having a first leading end, a first trailing end, and an intermediate portion extending therebetween. A second flange member includes a second leading end, a second trailing end, and an intermediate section extending therebetween. A first leg portion includes a first end extending from the first flange member, and a second end. A second leg portion has a first end portion extending from the second flange member, and a second end portion. A wing member is arranged between the first and second leg portions at respective ones of the second end and second end portions. The wing member includes a flow conditioning surface having a non-linear profile extending between the second end and the second end portion.

Abstract: A flow mixing lobe for an exhaust diffuser includes a first flange member having a first leading end, a first trailing end, and an intermediate portion extending therebetween. A second flange member includes a second leading end, a second trailing end, and an intermediate section extending therebetween. A first leg portion includes a first end extending from the first flange member, and a second end. A second leg portion has a first end portion extending from the second flange member, and a second end portion. A wing member is arranged between the first and second leg portions at respective ones of the second end and second end portions. The wing member includes a flow conditioning surface having a non-linear profile extending between the second end and the second end portion.

Abstract: A shim assembly includes a shim having a first side and a second side, at least one of the first side and the second side being oriented to form a wedge-shaped shim. Also included is a threaded fastener operatively coupled to the shim and configured to translate the shim in a direction parallel to a longitudinal direction of the threaded fastener.

Abstract: An inspection hole and plug are provided for an outer casing of a turbomachine. The plug includes an attachment portion configured to removably attach the plug to a coupling portion of the inspection hole. Additionally, the plug includes a tightening portion, a lock nut, and a rod extending through the plug. The lock nut is configured to removably attach the rod to the tightening portion of the plug. The rod also extends into a body of the inspection hole. Further, the inspection hole includes a stepped end positioned proximate to an inner surface of the outer casing to prevent the rod from extending through the outer casing of the turbomachine.

Abstract: A thrust bearing support assembly includes a first substantially trapezoidally-shaped side, and a second substantially rectangularly-shaped side coupled to the first side. The thrust bearing support assembly also includes a third substantially trapezoidally-shaped side coupled to the second side, and a fourth substantially rectangularly-shaped side coupled to the first and third sides.

Abstract: A glass breaking cap for flashlights, batons and the like is provided. The glass breaking cap has a cylindrical sidewall and a conical top portion. The conical top portion has an apex having an included angle between 86° and 136°. More preferably, the apex has an included angle of 106° to 126° with a preferred included angle of about 116°. Preferably, the glass breaking cap has male or female threads for replacing threaded end caps found on traditional flashlights and batons.

Abstract: A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a frusto-conically shaped structural support such that the net axial thrust of the coupled core gas turbine engine and power turbine reacts through the thrust bearing support assembly at engine centerline to facilitate minimizing distortion of the core gas turbine engine casing, and supporting the thrust bearing support assembly such that all of the remaining thrust generated by the core gas turbine engine and the power turbine is reacted to ground.

Abstract: A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a frusto-conically shaped structural support such that the net axial thrust of the coupled core gas turbine engine and power turbine reacts through the thrust bearing support assembly at engine centerline to facilitate minimizing distortion of the core gas turbine engine casing, and supporting the thrust bearing support assembly such that all of the remaining thrust generated by the core gas turbine engine and the power turbine is reacted to ground.

Abstract: A glass breaking cap for flashlights, batons and the like is provided. The glass breaking cap has a cylindrical sidewall and a conical top portion. The conical top portion has an apex having an included angle between 86° and 136°. More preferably, the apex has an included angle of 106° to 126° with a preferred included angle of about 116°. Preferably, the glass breaking cap has male or female threads for replacing threaded end caps found on traditional flashlights and batons.