Abstract: A lubrication system for a gas turbine engine is provided. The lubrication system includes a supply source of a fluid lubricant, a main supply pump, and a boost pump system. The main supply pump has an MSP fluid flow inlet port and an MSP fluid flow exit port. The main supply pump is configured to receive a source fluid lubricant flow at a first pressure, and configured to produce a supply fluid flow at a second pressure. The second pressure is greater than the first pressure. The boost pump system has a boost pump having a BP fluid flow inlet port, and a BP fluid flow exit port. The boost pump system is configured so that the boost pump selectively receives at least a portion of the supply fluid flow from the main supply pump at the BP fluid flow inlet port, and the boost pump is configured to produce a boost supply fluid flow at a third pressure at the BP fluid flow exit port, wherein the third pressure is greater than the second pressure.

Abstract: A lubrication system for a gas turbine engine is provided. The lubrication system includes a supply source of a fluid lubricant, a main supply pump, and a boost pump system. The main supply pump has an MSP fluid flow inlet port and an MSP fluid flow exit port. The main supply pump is configured to receive a source fluid lubricant flow at a first pressure, and configured to produce a supply fluid flow at a second pressure. The second pressure is greater than the first pressure. The boost pump system has a boost pump having a BP fluid flow inlet port, and a BP fluid flow exit port. The boost pump system is configured so that the boost pump selectively receives at least a portion of the supply fluid flow from the main supply pump at the BP fluid flow inlet port, and the boost pump is configured to produce a boost supply fluid flow at a third pressure at the BP fluid flow exit port, wherein the third pressure is greater than the second pressure.

Abstract: The present invention relates to a bleed deflector for a gas turbine engine. The bleed deflector comprises an inlet portion for receiving bleed air from the engine, a perforated top plate for discharging the bleed air into a duct, and an aerodynamically shaped strut for positioning the perforated top plate above an inner wall of the duct to allow dilution air to flow beneath the top plate.

Abstract: The present invention relates to a bleed deflector for a gas turbine engine. The bleed deflector comprises an inlet portion for receiving bleed air from the engine, a perforated top plate for discharging the bleed air into a duct, and an aerodynamically shaped strut for positioning the perforated top plate above an inner wall of the duct to allow dilution air to flow beneath the top plate.

Abstract: A mount for a gearbox accessory for a gas turbine engine substantially isolates the accessory from direct mechanical loading from the engine case during normal engine operating conditions and couples the accessory to the engine case during high rotor imbalance conditions to minimize interface loads between the gearbox and the accessory. By coupling the gearbox to the accessory, the two are displaced substantially in unison, thereby minimizing interface stresses therebetween. Various construction details of the mount for the gearbox accessories are disclosed.