Abstract: An anti-flow interruption system is configured to provide a supply of fuel in the event of a fuel flow interruption from a fuel tank. The anti-flow interruption system includes a reservoir, a reservoir conduit, and a vapor bleed system. The reservoir conduit has an end disposed at the bottom of the reservoir and another connected to a fuel pump. The vapor bleed system includes a vapor bleed conduit and a vapor bleed restrictor. One end of the vapor bleed conduit is attached to the top of the reservoir and the other end is connected to the fuel pump. The vapor bleed restrictor is disposed in the vapor bleed conduit between the fuel pump and the reservoir. If fuel flow is interrupted and results in vapor being present in the reservoir, liquid fuel remaining in the reservoir continues to be supplied to the fuel pump while the vapor bleed system removes the vapor.

Abstract: An anti-flow interruption system is configured to provide a supply of fuel in the event of a fuel flow interruption from a fuel tank. The anti-flow interruption system includes a reservoir, a reservoir conduit, and a vapor bleed system. The reservoir conduit has an end disposed at the bottom of the reservoir and another connected to a fuel pump. The vapor bleed system includes a vapor bleed conduit and a vapor bleed restrictor. One end of the vapor bleed conduit is attached to the top of the reservoir and the other end is connected to the fuel pump. The vapor bleed restrictor is disposed in the vapor bleed conduit between the fuel pump and the reservoir. If fuel flow is interrupted and results in vapor being present in the reservoir, liquid fuel remaining in the reservoir continues to be supplied to the fuel pump while the vapor bleed system removes the vapor.

Abstract: A fluid cooled seal arrangement for a gas turbine engine including a first sealing element coupled to a mechanical housing of the engine, and a second sealing element connected to a shaft rotatable within the housing. The first and second sealing elements are arranged radially adjacent to one another to form a rubbing interface therebetween. A lubrication system for delivering cooling fluid to the second sealing element through a passageway arranged along the rotating shaft. The cooling fluid is discharged through a plurality of openings formed in one end of the passageway. During normal operation of the engine the centrifugal force from the rotation of the shaft flings the oil radially outward to a channel formed on the underside of the second sealing element. The channel receives the cooling fluid therein, and allows for the escape of the cooling fluid onto the underside of the second sealing element to provide a uniform thickness of cooling fluid thereon.

Abstract: An accessory drive spline lubrication system for a turbine engine reduction gearbox prevents the continuing loss of engine oil resulting from an ineffective seal between an engine drive shaft and an accessory driven shaft. The spline area is provided with oil by an annular reservoir which is replenished only on startup of the engine. Oil is shot into the annular reservoir within the drive shaft through an orifice in the rotating drive shaft. At operating speeds, the drive shaft rotates sufficiently fast relative to the velocity at which the oil approaches the drive shaft to prevent the oil from entering the drive shaft.

Abstract: A secondary oil system for a gas turbine engine includes a dual phase blocking member in a passage between an oil reservoir and a secondary orifice adjacent a bearing of the engine. The blocking member has a first phase at temperatures below a threshold temperature of the bearing in which the blocking member prevents secondary oil flow and a second phase at temperatures above the threshold temperature in which the blocking member permits secondary oil flow. Normally, primary oil flow maintains the bearing at an operating temperature below the threshold temperature so that secondary oil flow is normally blocked. After primary oil flow stops, the bearing temperature increases to the threshold temperature and the blocking member transitions to its second phase to initiate secondary lubrication.

Abstract: A secondary oil system for a flight propulsion gas turbine engine having a vertical flight mode and a horizontal flight mode.