Abstract: A gas turbine engine includes a high speed turbine and a high speed compressor connected by a high speed shaft to define a high speed spool. A low speed turbine and a low speed compressor are connected by a low speed shaft to define a low speed spool. A high speed tower shaft is driven by the high speed spool and a low speed tower shaft is driven by the low speed spool. The low speed tower shaft drives a low speed input gear in an accessory drive differential. The high speed tower shaft drives a high speed input gear in the accessory drive differential. One of the high speed input gear and the low speed input gear increases an output speed of an output gear, and the other decreases an output speed of the output gear. The output gear drives at least one accessory for the gas turbine engine.

Abstract: A fluid filtration assembly (FFA) includes a housing having a thickness defined between an internal surface and an external surface, the housing receiving a filter and defining an outer annular flow passage between an outer surface of the filter and the internal surface of the housing; an inlet pipe communicates with the FFA and injects a fluid into the housing to impart a centrifugal force; an outlet pipe communicates with the FFA and discharges the fluid from the housing; and a collection area disposed towards an end of the outer annular flow passage collects particulate matter from the fluid; wherein a width of the outer annular flow passage increases towards the collection area.

Abstract: A fluid filtration assembly (FFA) includes a housing having a thickness defined between an internal surface and an external surface, the housing receiving a filter and defining an outer annular flow passage between an outer surface of the filter and the internal surface of the housing; an inlet pipe communicates with the FFA and injects a fluid into the housing to impart a centrifugal force; an outlet pipe communicates with the FFA and discharges the fluid from the housing; and a collection area disposed towards an end of the outer annular flow passage collects particulate matter from the fluid; wherein a width of the outer annular flow passage increases towards the collection area.

Abstract: An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.

Abstract: An oil tank for a gas turbine engine includes a top and a bottom disposed vertically beneath the top. An overfill return passage extends from the bottom of the oil tank toward the top of the oil tank. An outlet is formed on the bottom of the oil tank and inside the overfill return passage. A check valve is inside the overfill return passage and is connected to the outlet. The check valve includes a seat circumscribing the outlet and a plug inside the overfill return passage. The plug has a lower density than an oil disposed inside the oil tank. The check valve does not include a spring such that the plug is configured to translate freely inside the overfill return passage.

Abstract: A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor. The gear train is coupled through an engine accessory to an engine accessory gearbox that is further coupled to a starting spool of the engine. The bowed rotor prevention motor is operable to drive rotation of the starting spool of the gas turbine engine through the gear train upon engine shutdown.

Abstract: A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor operable to drive rotation of a starting spool of the gas turbine engine through the gear train at a substantially constant speed upon engine shutdown until an energy storage source is depleted.

Abstract: A fluid filtration assembly (FFA) includes a housing having a thickness defined between an internal surface and an external surface, the housing receiving a filter and defining an outer annular flow passage between an outer surface of the filter and the internal surface of the housing; an inlet pipe communicates with the FFA and injects a fluid into the housing to impart a centrifugal force; an outlet pipe communicates with the FFA and discharges the fluid from the housing; and a collection area disposed towards an end of the outer annular flow passage collects particulate matter from the fluid; wherein a width of the outer annular flow passage increases towards the collection area.

Abstract: An oil tank for a gas turbine engine includes a top and a bottom disposed vertically beneath the top. An overfill return passage extends from the bottom of the oil tank toward the top of the oil tank. An outlet is formed on the bottom of the oil tank and inside the overfill return passage. A check valve is inside the overfill return passage and is connected to the outlet. The check valve includes a seat circumscribing the outlet and a plug inside the overfill return passage. The plug has a lower density than an oil disposed inside the oil tank. The check valve does not include a spring such that the plug is configured to translate freely inside the overfill return passage.

Abstract: A gas turbine engine includes a turbine section configured to rotate about an engine axis relative to an engine static structure. A fan section is configured to rotate about the engine axis relative to the engine static structure. A geared architecture operatively connects the fan section to the turbine section. The geared architecture includes an input gear and an output gear both configured to rotate about the engine axis. A set of idler gears are arranged radially outward relative to and operatively coupling with the input and output gears.

Abstract: An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.

Abstract: An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.

Abstract: A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor. The gear train is coupled through an engine accessory to an engine accessory gearbox that is further coupled to a starting spool of the engine. The bowed rotor prevention motor is operable to drive rotation of the starting spool of the gas turbine engine through the gear train upon engine shutdown.

Abstract: A bowed rotor prevention system for a gas turbine engine of an aircraft is provided. The bowed rotor prevention system includes a gear train and a bowed rotor prevention motor operable to drive rotation of a starting spool of the gas turbine engine through the gear train at a substantially constant speed upon engine shutdown until an energy storage source is depleted.

Abstract: An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.

Abstract: A gas turbine engine includes a turbine section configured to rotate about an engine axis relative to an engine static structure. A fan section is configured to rotate about the engine axis relative to the engine static structure. A geared architecture operatively connects the fan section to the turbine section. The geared architecture includes an input gear and an output gear both configured to rotate about the engine axis. A set of idler gears are arranged radially outward relative to and operatively coupling with the input and output gears.