Patent application number | Description | Published |
20120087780 | INTEGRATED ACTUATOR MODULE FOR GAS TURBINE ENGINE - An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing. | 04-12-2012 |
20120171018 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15. | 07-05-2012 |
20120198815 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine. | 08-09-2012 |
20120198816 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages. | 08-09-2012 |
20120198817 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train. | 08-09-2012 |
20120233982 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages. | 09-20-2012 |
20120234017 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion. | 09-20-2012 |
20120315130 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the high pressure compressor section is between about 7 and about 15, and a pressure ratio across the fan section is less than or equal to 1.45. | 12-13-2012 |
20130014489 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train. | 01-17-2013 |
20130014490 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine. | 01-17-2013 |
20130086922 | Combined Pump System for Engine TMS AOC Reduction and ECS Loss Elimination - A compression pump for an engine is provided. The pump may include a first impeller operatively coupled to a main shaft of the engine, a first inlet configured to at least partially receive bypass airflow, and a first outlet configured to direct compressed air to a thermal management system. | 04-11-2013 |
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 |
20130098047 | COMPARTMENT COOLING FOR A GAS TURBINE ENGINE - A gas turbine engine includes a first pump driven by a spool, an air-oil cooler downstream of the first pump. A second pump driven by the spool and an air-air precooler downstream of the second pump, the air-air precooler downstream of the air-oil cooler. A compartment is downstream of the precooler to receive a cooling air from the precooler. | 04-25-2013 |
20130098057 | CONTROLLABLE SPEED WINDMILL OPERATION OF A GAS TURBINE ENGINE THROUGH LOW SPOOL POWER EXTRACTION - A gas turbine engine that includes at least one component geared to a spool to control a speed of the low spool during a “windmilling” condition. | 04-25-2013 |
20130098059 | WINDMILL OPERATION OF A GAS TURBINE ENGINE - A gas turbine engine according to an exemplary aspect of the present disclosure includes a windmill pump driven by a spool. | 04-25-2013 |
20130098060 | GAS TURBINE ENGINE ONBOARD STARTER/GENERATOR SYSTEM TO ABSORB EXCESS POWER - A gas turbine engine includes an Integrated Drive Generator (IDG) geared to a low spool to selectively accelerate the low spool during a transient condition. | 04-25-2013 |
20130098067 | CONSTANT SPEED TRANSMISSION FOR GAS TURBINE ENGINE - A gas turbine engine includes a constant speed transmission driven by a spool. | 04-25-2013 |
20130108413 | SECONDARY FLOW ARRANGEMENT FOR SLOTTED ROTOR | 05-02-2013 |
20130108445 | SPOKED ROTOR FOR A GAS TURBINE ENGINE | 05-02-2013 |
20130108466 | ASYMETRICALLY SLOTTED ROTOR FOR A GAS TURBINE ENGINE | 05-02-2013 |
20130115057 | MID-TURBINE BEARING SUPPORT - A bearing assembly for a gas turbine engine includes a bearing, an outer assembly disposed about an axis and having an angled perimeter, and an inner assembly supporting the bearing and having a surface angled to slide against and attach to the angled perimeter as the bearing is aligned with the axis. | 05-09-2013 |
20130145774 | ACCESSORY GEARBOX WITH TOWER SHAFT REMOVAL CAPABILITY - An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis and includes first and second sides. A first geartrain includes one or more shafts rotatable about axes perpendicular to the first side of the accessory gearbox and a second geartrain includes one or more shafts rotatable about axes perpendicular to the second side of the accessory gearbox. A driven gear set defines an input axis and drives first geartrain and the second geartrain about corresponding first and second drive axes parallel to the input axis. | 06-13-2013 |
20130156542 | ENERGY-ABSORBING FAN CASE FOR A GAS TURBINE ENGINE - A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis and a plurality of helical ribs adjacent to the fan blade containment section. | 06-20-2013 |
20130174573 | ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT UTILIZING TURBO-COMPRESSOR - An environmental control system includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with a gas turbine engine. A lower pressure tap is associated with a lower pressure location, which is at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into the turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section of the turbocompressor and the turbine section intermix and pass downstream to be delivered to an aircraft use. | 07-11-2013 |
20130193688 | BEVEL GEAR ARRANGEMENT FOR AXIAL ACCESSORY GEARBOX - An accessory box for a gas turbine engine has an input gear to be driven by an input shaft. The input gear is engaged to drive a first driven gear on one radial side of a drive axis of the input gear. The first gear drives at least a second driven gear on one radial side of the drive axis, with at least one accessory driven by one of the first and second driven gears. The second driven gear drives a bevel gear arrangement to drive a third driven gear on an opposed side of the drive axis of the input gear. The third driven gear drives at least a second accessory. The accessories are associated with a gas turbine engine. | 08-01-2013 |
20130202415 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. The engine includes a combination of quantities providing beneficial operation. | 08-08-2013 |
20130205747 | GAS TURBINE ENGINE WITH MODULAR CORES AND PROPULSION UNIT - A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed. | 08-15-2013 |
20130205752 | GAS TURBINE ENGINE WITH SEPARATE CORE AND PROPULSION UNIT - A gas turbine engine includes a propulsion unit mounted to rotate about a first axis, and a core engine mounted to rotate about a second axis, and wherein the first and second axes are non-parallel. A gas turbine engine includes a propulsion unit driven by a free turbine which is adjacent to the propulsion unit and an associated fan, and having a gas generator core engine including a compressor, combustor and turbine section. A method is also disclosed. | 08-15-2013 |
20130239587 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. | 09-19-2013 |
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 |
20140150440 | GAS TURBINE ENGINE WITH A LOW SPEED SPOOL DRIVEN PUMP ARRANGEMENT - A gas turbine engine includes, among other things, a propulsion assembly situated to rotate about an engine central axis. Operation of the propulsion assembly requires a first amount of fluid during a first operating condition and a second, greater amount of the fluid during a second operating condition. A first pump is operatively associated with a low speed spool that rotates with a low pressure turbine. The first pump has a first fluid delivering capacity corresponding to at least the first amount. A second pump has a second fluid delivering capacity configured to correspond to at least a difference between the first amount and the second amount. The first pump provides the fluid for propulsion assembly during the first and second operating conditions and the second pump provides the fluid for propulsion assembly operation only during the second operating condition. | 06-05-2014 |
20140157752 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. The pressure ratio across the first compressor is greater than or equal to about 7. | 06-12-2014 |
20140157753 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. An overall pressure ratio, being provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor, is greater than or equal to about 35. The pressure ratio across the first compressor is greater than or equal to about 7. | 06-12-2014 |
20140157754 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. A pressure ratio across the fan section is less than or equal to about 1.50. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. | 06-12-2014 |
20140157755 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section is greater than or equal to about 8. | 06-12-2014 |
20140157756 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, the geared arrangement defining a gear reduction ratio greater than or equal to about 2.6. A compressor section includes both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. | 06-12-2014 |
20140157757 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. The turbine section includes a fan drive turbine configured to drive the fan section, a pressure ratio across the fan drive turbine being greater than or equal to about 5. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. | 06-12-2014 |
20140165534 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than or equal to about 8. | 06-19-2014 |
20140174056 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine comprises a gear train defined along an axis. A spool along the axis drives the gear train and includes a low stage count low pressure turbine. A fan i s rotatable at a fan speed about the axis and driven by the low pressure turbine through the gear train. The fan speed is less than a speed of the low pressure turbine. A core is surrounded by a core nacelle defined about the axis. A fan nacelle i s mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10). | 06-26-2014 |