General Electric Company

Ryan T Roehm

Brandon Wayne Miller

Arthur William Sibbach

Jeffrey Douglas Rambo

Scott Hunter

Duane Howard Anstead

Narendra Anand Hardikar

Andrew Hudecki

Donald Scott Yeager

John C Schilling

Pravin Ganpati Patil

Robert Eugene Dyson

Andrew Gumpert

A turbine engine includes a first gearbox, lubricated by oil. A first sump, located below the first gearbox, collects the oil. A first scavenge element pumps the oil from the first sump in an operational state and does not pump the oil in a failure state. A second gearbox is also lubricated by oil. A second sump, located below the second gearbox, collects the oil. A second scavenge element pumps the oil from the second sump in both the operational state and in the failure state. A conduit connects the first sump to the second sump to transfer overflow oil from the first sump to the second sump in the failure state, the overflow oil combining with the oil in the second sump, upon the oil in the first sump reaching a threshold level.

Turbine engine including a lubrication system

Fluid-filled thrust link apparatus and associated method are disclosed. A thrust link for an aircraft engine includes a first wall having a forward portion and an aft portion at opposite ends of the thrust link, the forward portion coupled to the aircraft engine, the aft portion coupled to the aircraft engine, a pylon, or an aircraft associated with the aircraft engine, and a second wall within an interior area surrounded by the first wall, the second wall spaced apart from the first wall, a space between the first wall and the second wall defining a channel within the interior area, the channel including a fluid, the fluid pressurized based on a damping ratio to withstand a resonant vibration frequency generated by the aircraft engine.

Fluid-filled thrust link apparatus and associated method

A turbine engine having a longitudinal centerline axis. The turbine engine including a fan comprising a plurality of fan blades that rotate about the longitudinal centerline axis and a rotational component coupled to the fan. The turbine engine including a fluid circuit for supplying fuel or lubricant to the turbine engine and a hydraulic fan brake coupled to the fluid circuit to prevent rotation of the rotational component, thus preventing rotation of the fan. The hydraulic fan brake including a hydraulic cylinder fluidly coupled to the fluid circuit and a valve coupled to the hydraulic cylinder and having a first valve position that disengages the hydraulic fan brake to allow rotation of the rotational component and a second valve position that engages the hydraulic fan brake to prevent rotation of the rotational component.

Gas turbine engine having a hydraulic fan brake

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.

Gearbox assembly lubrication system for a turbine engine

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West Chester, OH, United States of America

Ryan T Roehm