Patent application number | Description | Published |
20080236951 | OIL SCAVENGE SYSTEM HAVING CHURNING DAMPER FOR GAS TURBINE ENGINES - An oil scavenge system of a gas turbine engine in accordance with one embodiment of the present invention, comprises a housing defined about an axis of rotation, the housing confining an air/oil mixture in motion within the housing and defining an oil scavenge area below the axis of rotation. The housing further includes an outlet at a low location of the housing. A churning damper is supported within the housing and is located in the oil scavenge area. The churning damper includes at least one plate, allowing the air/oil mixture in motion to pass over or through the plate only in a peripheral area of the at least one plate to cause flow energy dissipation. | 10-02-2008 |
20090101444 | GAS TURBINE OIL SCAVENGING SYSTEM - A method for scavenging oil in a gas turbine engine comprises using a driving fluid flow to drive a flow of a fluid collected in an oil system of the engine to pass through an ejector and then the driven flow of the fluid is directed to be discharged into an oil tank. | 04-23-2009 |
20100272556 | LOAD DISTRIBUTION SYSTEM FOR GAS TURBINE ENGINE - There is provided an axial bearing load distribution system for a gas turbine engine of the type having a low pressure rotor supported by axial bearings. The system comprises a line having an inlet end positioned in a high-pressure compressor gas path downstream of any compressor stage provided with a variable geometry. The line is adapted to sense static pressure in the high-pressure compressor gas path. The line has an outlet end producing the static pressure. An air-tight pressure actuator is operatively connected to the outlet end and to one of the axial bearings to exert a force on the axial bearing proportionally to a pressure of the outlet end. | 10-28-2010 |
20110067413 | EJECTOR CONTROLLED TWIN AIR SOURCE GAS TURBINE PRESSURIZING AIR SYSTEM - A passive pressurizing air system for a gas turbine engine includes a flow path for directing an air flow having a low temperature and low pressure, extending through a cavity to a pressurized area of the engine. The cavity contains pressurized air having a high temperature and high pressure. An air flow mixing apparatus is provided for adding the pressurized air from the cavity into the flow path to provide a mixed air flow having an intermediate temperature and intermediate pressure. | 03-24-2011 |
20120060508 | GAS TURBINE ENGINE BREATHER EXHAUST OIL COLLECTOR - A gas turbine engine oil system has an air-oil separator for removing air from an air/oil mixture. A breather tube is connected to an exhaust of the air-oil separator for receiving hot air removed from the air/oil mixture in the air-oil separator. The gas turbine engine oil separator exhaust is directed in a cooled oil collector to cause the oil mist remaining in the air at the exit from the engine air-oil separator to condensate. The oil condensate is returned back into the engine oil system. | 03-15-2012 |
20120181113 | OIL SCAVENGE SYSTEM HAVING CHURNING DAMPER FOR GAS TURBINE ENGINES - An oil scavenge system of a gas turbine engine in accordance with one embodiment of the present invention, comprises a housing defined about an axis of rotation, the housing confining an air/oil mixture in motion within the housing and defining an oil scavenge area below the axis of rotation. The housing further includes an outlet at a low location of the housing. A churning damper is supported within the housing and is located in the oil scavenge area. The churning damper includes at least one plate, allowing the air/oil mixture in motion to pass over or through the plate only in a peripheral area of the at least one plate to cause flow energy dissipation. | 07-19-2012 |
20130199152 | TURBINE ENGINE HEAT RECUPERATOR PLATE AND PLATE STACK - A heat recuperator includes a plurality of channel walls composed substantially of thermally-conductive material and supported in spaced-apart relation, defining fluid channels and interstices therebetween. The fluid channels receive at least one primary fluid flow and the interstices receive at least one secondary fluid flow so as to effect heat exchange between the two flows. In use, the plurality of channel walls are deformable by pressure differential between the primary and secondary fluid flows. When at least some of the channel walls are in a deformed state, the plurality of channel walls are stabilized through press fit engagement of mutually opposed contact regions formed in adjacent pairs of the channel walls. | 08-08-2013 |
20130219854 | AIR-COOLED OIL COOLER FOR TURBOFAN ENGINE - A turbofan gas turbine engine comprises a nacelle cowl and a core engine. A bypass duct is between an outer surface of a casing of the core engine, and an inner surface of the nacelle cowl. An air channel is in the nacelle cowl, an inlet and an outlet of the air channel being in an outer surface of the nacelle cowl. An oil cooler has at least one oil passage for oil circulation, the air cooler having a first heat exchange surface in the air channel exposed to air circulating in the air channel, the air channel having a second heat exchange surface in the bypass duct exposed to air circulating in the bypass duct. A method for cooling oil in a turbofan gas turbine engine is also provided. | 08-29-2013 |