A lubricant system for supplying lubrication to a component in a turbine engine includes a lubricant reservoir, a supply line fluidly coupling the lubricant reservoir to the component in the turbine engine, a scavenge line fluidly coupling the component to the lubricant reservoir, and a bypass line fluidly coupling the supply line to the scavenge line and bypassing the component.

A lubricant system for supplying lubrication to a component in a turbine engine includes a lubricant reservoir, a supply line fluidly coupling the lubricant reservoir to the component in the turbine engine, a scavenge line fluidly coupling the component to the lubricant reservoir, and a bypass line fluidly coupling the supply line to the scavenge line and bypassing the component.

A system for a turbine engine includes a first bearing, a second bearing, a first rotating assembly, a second rotating assembly, a first lubrication circuit and a second lubrication circuit. The first rotating assembly includes a first component rotatably supported by the first bearing. The second rotating assembly includes a second component rotatably supported by the second bearing. The first lubrication circuit includes a first pump and the first bearing. The first pump is driven by the first rotating assembly and configured to pump lubricant to the first bearing. The second lubrication circuit includes a second pump and the second bearing. The second pump is configured to pump lubricant to the second bearing. The second lubrication circuit is configured discrete from the first lubrication circuit.

A system for a turbine engine includes a first bearing, a second bearing, a first rotating assembly, a second rotating assembly, a first lubrication circuit and a second lubrication circuit. The first rotating assembly includes a first component rotatably supported by the first bearing. The second rotating assembly includes a second component rotatably supported by the second bearing. The first lubrication circuit includes a first pump and the first bearing. The first pump is driven by the first rotating assembly and configured to pump lubricant to the first bearing. The second lubrication circuit includes a second pump and the second bearing. The second pump is configured to pump lubricant to the second bearing. The second lubrication circuit is configured discrete from the first lubrication circuit.

A lubrication system for a turbopropeller, includes an oil feed device for at least one enclosure and one equipment, the equipment being connected to the feed device via a displacement pump, and a pressure restricting valve mounted downstream of displacement pump and in parallel to the equipment, such that oil flows through the equipment when the same is active, and through the valve when the equipment is inactive.

A lubrication system for a turbopropeller, includes an oil feed device for at least one enclosure and one equipment, the equipment being connected to the feed device via a displacement pump, and a pressure restricting valve mounted downstream of displacement pump and in parallel to the equipment, such that oil flows through the equipment when the same is active, and through the valve when the equipment is inactive.

An actuator includes a housing, a first chamber inside the housing, a cylinder within the housing, and a second chamber within the housing. The cylinder fluidically isolates the first chamber from the second chamber. The actuator also includes a rod connected to the cylinder and extending through the second chamber and the housing. A shell is spaced apart from the housing and defines a fluid gap between the shell and the housing. The shell includes a shell inlet fluidically connected to the fluid gap and a shell outlet fluidically connected to the fluid gap.

A fluid viscosity system for use in a gas turbine engine includes an induction assembly coupled to a fluid line within the gas turbine engine. The induction assembly includes an electromagnet. The induction assembly further includes an electronic oscillator electronically coupled to the electromagnet. The electronic oscillator is configured to generate an alternating current (AC) that is transmitted to the electromagnet at a predetermined frequency and magnitude such that a viscosity of a fluid channeled through the fluid line is reduced at least partially due to induction heating.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.