Abstract: A lubrication system for a turbine engine having a longitudinal centerline axis and one or more rotating components. The lubrication system includes a primary lubrication system that supplies lubricant to the one or more rotating components during normal operation of the turbine engine. The lubrication system also includes an auxiliary lubrication system. The auxiliary lubrication system includes an auxiliary reservoir and a lubricant dispersion device. The auxiliary reservoir stores the lubricant therein. The lubricant dispersion device rotates about the longitudinal centerline axis. The lubricant dispersion device collects the lubricant in the auxiliary reservoir and disperses the lubricant to the one or more rotating components as the lubricant dispersion device rotates.

Abstract: A lubrication system for a turbine engine having a longitudinal centerline axis and one or more rotating components. The lubrication system includes a primary lubrication system that supplies lubricant to the one or more rotating components during normal operation of the turbine engine. The lubrication system also includes an auxiliary lubrication system. The auxiliary lubrication system includes an auxiliary reservoir and a lubricant dispersion device. The auxiliary reservoir stores the lubricant therein. The lubricant dispersion device rotates about the longitudinal centerline axis. The lubricant dispersion device collects the lubricant in the auxiliary reservoir and disperses the lubricant to the one or more rotating components as the lubricant dispersion device rotates.

Abstract: A method of operating a lubrication system for a turbine engine having a fan and one or more rotating components. The lubrication system includes a primary lubrication system and an auxiliary lubrication system. The method includes supplying lubricant to the one or more rotating components from the primary lubrication system during a normal operation of the turbine engine, determining whether at least one of a fuel pressure is less than a fuel pressure threshold or a hydraulic pressure is less than a hydraulic pressure threshold, and activating the auxiliary lubrication system to supply the lubricant to the one or more rotating components from the auxiliary lubrication system when the fuel pressure is less than the fuel pressure threshold or the hydraulic pressure is less than the hydraulic pressure threshold.

Abstract: A lubrication system for a turbine engine. The turbine engine includes a fan having a fan shaft and one or more rotating components. The lubrication system includes one or more tanks that stores lubricant therein, a primary lubrication system, and an auxiliary lubrication system. The primary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump that is coupled to the fan shaft. The auxiliary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components based on a pressure of the lubricant in the primary lubrication system. Rotation of the fan shaft causes the auxiliary pump to pump the lubricant to the one or more rotating components.

Abstract: A lubrication system for a gearbox assembly for a turbine engine. The gearbox assembly includes a gear assembly including one or more gears and one or more bearings. The lubrication system includes a sump. The sump is a primary reservoir that has a first lubricant level. The lubrication system also includes a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level that is greater than the first lubricant level. A plurality of drain ports includes a first drain port and a second drain port. The lubrication system fills the secondary reservoir with lubricant between the first lubricant level and the second lubricant level and a portion of the lubricant drains though the second drain port. The one or more gears collects the lubricant to supply the lubricant from the secondary reservoir to the one or more gears or to the one or more bearings.

Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.

Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.

Abstract: A gas turbine engine includes a rotatably driven engine component including a shaft coupling. The shaft coupling defines a first axial centerline and includes an inner surface. The inner surface includes a plurality of internal splines extending radially inwardly from the inner surface with respect to the first axial centerline. The engine further includes a driving member having a driving end portion and defining a second axial centerline. The driving end portion includes an outer surface and a plurality of external splines extending radially outwardly from the outer surface with respect to the second axial centerline. The plurality of external splines is drivingly engaged with the plurality of internal splines. The plurality of internal splines or the plurality of external splines comprises bowed splines.

Abstract: A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.

Abstract: A gas turbine engine is provided. The gas turbine engine includes: a fan; a turbomachine drivingly coupled to the fan and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine, the turbomachine defining an annular cooling passage extending between a CP inlet and a CP outlet, the CP inlet in airflow communication with the working gas flowpath and the CP outlet in airflow communication with the bypass passage; and a variable bleed assembly including a variable bleed duct extending between a VB inlet and a VB outlet, the VB inlet in airflow communication with the working gas flowpath at a location downstream of the CP inlet and the VB outlet in airflow communication with the annular cooling passage for urging an airflow through the cooling passage.