Patent application number | Description | Published |
20110289936 | ACCESSORY GEARBOX WITH INTERNAL LAYSHAFT - An engine accessory system for a gas turbine engine includes a first accessory component mountable to an accessory gearbox along a first accessory axis transverse to a layshaft axis of rotation. | 12-01-2011 |
20120117981 | AXIAL ACCESSORY GEARBOX - An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis. A crossover gear set generally along the accessory gearbox axis interconnects a first gear set and a second gear set. | 05-17-2012 |
20120117982 | AXIAL ACCESSORY GEARBOX - An accessory system for a gas turbine engine includes a main case which defines an accessory gearbox axis. A cover is removably mountable to the main case and a first gear set at least partially within the cover along a first accessory axis transverse to the accessory gearbox axis. | 05-17-2012 |
20130047624 | DISTRIBUTED LUBRICATION SYSTEM - A gas turbine engine includes a spool, a gearbox having gearing driven by the spool, and a lubrication system. The lubrication system includes a first heat exchanger positioned in a first air flow path, a second heat exchanger positioned in a second air flow path, and a lubrication pump fluidically connected to both the first heat exchanger and the second heat exchanger. A first air fan is driven by the gearbox for inducing air flow through the first air flow path. A second air fan is driven by an electric motor for inducing air flow through the second air flow path. | 02-28-2013 |
20130097992 | INTEGRATED THERMAL MANAGEMENT SYSTEM AND ENVIRONMENTAL CONTROL SYSTEM FOR A GAS TURBINE ENGINE - A gas turbine engine includes a first and second pump driven by a spool. An Air-Oil Cooler downstream of the first pump. An air-air precooler is downstream of the second pump, the air-air precooler downstream of the Air-Oil Cooler. | 04-25-2013 |
20130098046 | INTEGRATED THERMAL SYSTEM FOR A GAS TURBINE ENGINE - An integrated thermal system for a gas turbine engine includes an Air-Oil Cooler and an Air-Air PreCooler within a housing, the Air-Air PreCooler downstream of the Air-Oil Cooler. | 04-25-2013 |
20130259638 | TURBOMACHINE THERMAL MANAGEMENT - An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior. | 10-03-2013 |
20130259639 | TURBOMACHINE THERMAL MANAGEMENT - An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump that is selectively driven by a motor or a shaft to communicate air to an interior of the nose cone. The pump shaft is driven by a dedicated geared architecture. | 10-03-2013 |
20130259687 | TURBOMACHINE THERMAL MANAGEMENT - An example turbomachine assembly includes, among other things, a nose cone of a turbomachine. The nose cone provides an aperture that communicates air to an interior of the nose cone. | 10-03-2013 |
20130291514 | GAS TURBINE ENGINE OIL TANK - A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. Fan and core nacelles define an annular bypass flow path. The core nacelle provides a core compartment and includes an opening into the core compartment. The oil tank is arranged in the core compartment and includes a portion aligned with the opening that is exposed to the bypass flow path. The engine static structure is supported relative to a fan case by a radial structure. The oil tank is mounted to the engine static structure. An oil fill tube is mounted to the fan case and is fluidly connected to the oil tank. | 11-07-2013 |
20140010639 | GAS TURBINE ENGINE OIL TANK WITH INTEGRATED PACKAGING CONFIGURATION - A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources. | 01-09-2014 |
20140096534 | Low Profile Compressor Bleed Air-Oil Coolers - An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed. | 04-10-2014 |
20140133973 | POWER CABLE AND CONNECTOR ARRANGEMENT FOR A GAS TURBINE ENGINE - A gas turbine engine component assembly according to an exemplary aspect of the present disclosure includes, among other things, a nacelle including a moveable portion. A generator is configured to be received within a space established by the nacelle. A plurality of cables are at least partially supported on the moveable portion of the nacelle, the plurality of cables being selectively electrically coupled with the generator. | 05-15-2014 |
20140165588 | TURBO COMPRESSOR FOR BLEED AIR - A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air. | 06-19-2014 |