Patent application number | Description | Published |
20080209911 | Combination engines for aircraft - An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto. | 09-04-2008 |
20080267769 | GAS TURBINE ENGINE BLADE TIP CLEARANCE APPARATUS AND METHOD - A method for controlling blade tip clearance within a gas turbine engine includes the steps of providing a compressor having at least one first rotor assembly, each first rotor assembly having a plurality of blades with each blade having a blade tip, at least one first stator assembly disposed adjacent at least one first rotor assembly, and a shroud having at least one blade seal surface disposed radially outside of at least one first rotor assembly, wherein the blade tips in each of at least one first rotor assembly has a mating geometry with at least one of at least one blade seal surfaces, and a clearance distance extending between the blade tips and the blade seal surfaces; providing a turbine having at least one second rotor assembly, each second rotor assembly having a plurality of blades with each blade having a blade tip, at least one second stator assembly disposed adjacent at least one second rotor assembly, and the shroud having at least one blade seal surface disposed radially outside of at least one second rotor assembly, wherein the blade tips in each of at least one second rotor assembly has a mating geometry with at least one of at least one blade seal surfaces, and a clearance distance extending between the blade tips and the blade seal surfaces; providing an actuator selectively operable to move at least one rotor assembly relative to the shroud; providing an electronic engine controller having a control logic for operating the actuator; and moving at least one first rotor assemblies and at least one second rotor assembly relative to the shroud using the actuator at a response rate according to the control logic to alter the clearance distance. | 10-30-2008 |
20080277533 | Aircraft combination engines inlet airflow control system - A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft that is curved along its extent in leading to an air compressor in the gas turbine engine having a compressor air transfer duct extending therefrom to an internal combustion engine provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold is positioned against the duct wall of the inlet duct to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake. | 11-13-2008 |
20080277944 | Aircraft combination engines complemental connection and operation - A power generation system for propelling, and generating electrical power in, an aircraft, using a gas turbine engine coupled to a turbine starter/generator unit having therein an electrical machine capable of being selected to be alternatively a motor and an electrical power generator and having a coupling shaft extending therefrom to be engaged with the air compressor in the gas turbine engine and further having an interconnection conductor for electrical energization. An internal combustion engine provided as an intermittent combustion engine in the aircraft has an air intake coupled through an air transfer duct connected to the air compressor to allow the transfer of compressed air thereto, and has in connection therewith a supply starter/generator unit with a coupling shaft extending therefrom to be engaged with the intermittent combustion engine power shaft. An interconnection conductor therein for electrical energization is electrically interconnected with the turbine starter/generator unit interconnection conductor. | 11-13-2008 |
20080314573 | Aircraft combination engines thermal management system - An engine combination for generating forces with a gas turbine engine generating force that utilizes an engine lubricant for lubricating moving components in the turbofan engine, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force that utilizes a coolant for transporting heat generated in the intermittent combustion engine away therefrom and having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto. A coupling heat exchanger is coupled to both the gas turbine engine and the intermittent combustion engine to have the engine lubricant and the coolant pass therethrough to thereby permit the coolant to transport heat in the engine lubricant away therefrom. A further cooling heat exchanger is coupled to both the coupling heat exchanger and the intermittent combustion engine to have a remote fluid from a source thereof and the coolant pass therethrough to permit the remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the coupling heat exchanger and the intermittent combustion engine. | 12-25-2008 |
20090065652 | Aircraft combination engines exhaust thrust recovery - A gas turbine engine with a turbine with an exhaust manifold thereabout from which fluids can be transferred to the turbine and an air compressor having an air transfer duct extending therefrom so as to be capable to provide compressed air in that air transfer duct at one end thereof to the air intake of an internal combustion engine provided as an intermittent combustion engine. The air intake and an exhaust outlet are each coupled to combustion chambers therein and a rotatable output shaft is also coupled to those combustion chambers for generating force. The exhaust outlet has an exhaust transfer duct extending therefrom so as to have the intermittent combustion engine be capable to provide exhaust therefrom in that exhaust transfer duct at one end thereof, and the exhaust transfer duct being connected at an opposite end thereof to the exhaust manifold to be capable of transferring intermittent combustion engine exhaust thereto. | 03-12-2009 |
20090088063 | Cabin air supercharged aircraft internal combustion engine - An aircraft having a user region therein within which pressurized air at selected pressures can be maintained using an environmental control system provided in the aircraft, and a utility region outside a utility boundary wall of the user region within which selected equipment for the aircraft is located. An internal combustion engine, provided as an intermittent combustion engine, is provided in the utility region having an air intake coupled to combustion chambers therein and a rotatable output shaft also coupled to those combustion chambers for generating force with an air transfer duct extends between the user region and the air intake so as to be capable of conveying pressurized air to that air intake. | 04-02-2009 |
20100013242 | Aircraft combination engines plural airflow conveyances system - An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being a plurality of air transfer ducts each extending from a different location in the gas turbine engine so as to be capable to provide air in each of those air transfer ducts at one end thereof at pressures differing from one another and connected at the other end of each to the air intake to transfer air thereto. | 01-21-2010 |
20100275578 | COOLING EXCHANGER DUCT - A method for using a heat exchange system in operating equipment in which a working fluid is utilized in providing selected operations thereof, including for use in lubricating systems for aircraft turbofan engine equipment, the heat exchange system for providing air and working fluid heat exchanges to cool the working fluid at selectively variable rates in the operating equipment developed airstreams. A heat exchanger core is provided in a controlled air flow duct system opening at its entrance to those airstreams and having its outlet end opening downstream in those airstreams. | 11-04-2010 |
20120060466 | AIR-OIL HEAT EXCHANGER - A heat exchange system for use in fluid operated equipment to provide air and working fluid heat exchanges to cool the working fluid in airstreams on a stream side of a wall. An actuator is mounted to be substantially located on a side of the wall opposite the stream side thereof having a positionable motion effector. A heat exchanger core having a plurality of passageway structures therein to enable providing the working fluid to, and removal therefrom. The heat exchanger core is mounted on the motion effector so as to be extendable and retractable thereby through the opening for selected distances into that region to be occupied by the airstreams. | 03-15-2012 |
20120085528 | INTERDEPENDENT LUBRICATION SYSTEMS - A heat exchange system for use in operating equipment having a plurality of subsystems in each of which one of a plurality of working fluids is utilized to provide selected operations with there being an air and working fluid heat exchanger providing controlled cooling to cool at least one of the plurality of working fluids in its corresponding subsystem. In addition, a coupling heat exchanger is also provided connected to two of the subsystems to pass there working fluids therethrough, including the subsystem with the air and working fluid heat exchanger, to allow one of the connected subsystems to aid in cooling the other. | 04-12-2012 |
20120174593 | BLADES IN A TURBINE SECTION OF A GAS TURBINE ENGINE - An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in the low pressure turbine is from three to five. | 07-12-2012 |
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 |
20120213628 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A geared architecture with a flex mount for a fan drive gear system. | 08-23-2012 |
20120222397 | GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO - A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-06-2012 |
20120222398 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A turbofan engine includes a geared architecture and a fan variable area nozzle axially movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-06-2012 |
20120233981 | GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO - A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-20-2012 |
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 |
20120237334 | GAS TURBINE ENGINE GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3 | 09-20-2012 |
20120237335 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A geared architecture with a flex mount for a fan drive gear system. | 09-20-2012 |
20120237336 | GAS TURBINE ENGINE GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3 | 09-20-2012 |
20120238401 | EPICYCLIC GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. Each journal bearing includes an internal central cavity and at least one passage that extends radially from the internal cavity to a peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3. | 09-20-2012 |
20120243971 | EPICYCLIC GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. Each journal bearing includes an internal central cavity and at least one passage that extends radially from the internal cavity to a peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3. | 09-27-2012 |
20120275904 | GAS TURBINE ENGINE LUBRICATION - A turbine engine includes a fan shaft and at least one tapered bearing mounted on the fan shaft. The fan shaft includes at least one radially extending passage adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear, and a ring gear that surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3 | 11-01-2012 |
20120291449 | Turbine Section of High Bypass Turbofan - A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170. | 11-22-2012 |
20130004322 | FAN BLADE WITH SHEATH - A fan blade includes an airfoil with a leading edge and a trailing edge in a chordwise direction, a root and a tip in a spanwise direction; and a sheath with a solid portion to cover the leading edge and first and second flanks extending in the chordwise direction to bond to the pressure and suction sides of the airfoil, respectively. The dimensions of the sheath are varied with respect to the spanwise direction of the blade. | 01-03-2013 |
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 |
20130019585 | VARIABLE FAN INLET GUIDE VANE FOR TURBINE ENGINE - A turbine engine includes a compressor section, a combustor arranged in fluid-receiving communication with the compressor section, a turbine section arranged in fluid-receiving communication with the combustor and a gearbox assembly coupled to be driven by the turbine section. The gearbox assembly is located at an axial position that is aft of the compressor section. | 01-24-2013 |
20130094937 | GAS TURBINE ENGINE OIL BUFFERING - A turbine engine includes a shaft, a fan, at least one bearing mounted on the shaft and rotationally supporting the fan, a fan drive gear system coupled to drive the fan, a bearing compartment around the at least one bearing and a source of pressurized air in communication with a region outside of the bearing compartment. | 04-18-2013 |
20130111915 | SYSTEM FOR OPTIMIZING POWER USAGE FROM DAMAGED FAN BLADES - An aircraft jet engine system includes at least one gas turbine engine having a fan including a rotor and a plurality of fan blades. A sensor system in the fan section senses information about the operation of the blades and provides feedback on the condition of each blade to a control. The control is programmed to take in the sensed information and identify a safe operating range for the gas turbine engine based upon damage information developed from the sensed information with regard to each of the blades. An aircraft jet engine system incorporating a plurality of gas turbine engines wherein safe operating ranges are developed for each of the gas turbine engines is also disclosed as is a method of operating an aircraft jet engine system. | 05-09-2013 |
20130145745 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO - A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45. | 06-13-2013 |
20130149099 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE TO REDUCE FAN INSTABILITY - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area to reduce a fan instability. | 06-13-2013 |
20130149111 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 06-13-2013 |
20130149112 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 06-13-2013 |
20130149113 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO - A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45. | 06-13-2013 |
20130192191 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES - A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section. | 08-01-2013 |
20130192196 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION - A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. | 08-01-2013 |
20130192200 | GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE - A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine. | 08-01-2013 |
20130192201 | GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE - A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine. | 08-01-2013 |
20130192256 | GEARED TURBOFAN ENGINE WITH COUNTER-ROTATING SHAFTS - A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. The mid-turbine frame carries a plurality of vanes to redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine. In another feature, a power density is defined as the thrust divided by the volume of a turbine section, and the power density is of about 1.5 lbf per in | 08-01-2013 |
20130192258 | GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE - A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine. | 08-01-2013 |
20130192263 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION - A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. | 08-01-2013 |
20130192265 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES - A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted on the low pressure turbine with an intermediate bearing. | 08-01-2013 |
20130192266 | GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE - A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis. | 08-01-2013 |
20130195621 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES - A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section. | 08-01-2013 |
20130195624 | GEARED TURBOFAN ENGINE WITH COUNTER-ROTATING SHAFTS - A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. A plurality of vanes redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine. | 08-01-2013 |
20130195648 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES - A gas turbine engine includes a very high speed fan drive turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine. | 08-01-2013 |
20130219907 | GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY - A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction. | 08-29-2013 |
20130219908 | GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY - A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction. | 08-29-2013 |
20130219913 | GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION - A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a speed reduction. A sensor senses a speed of rotation of the fan and communicates sensed speed information to a control. The control develops an expected speed for the fan. A problem is identified should the sensed speed be less than the expected speed by more than a predetermined amount. A method is also described. | 08-29-2013 |
20130223974 | VARIABLE AREA TURBINE - A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition. | 08-29-2013 |
20130223986 | GAS TURBINE ENGINE WITH FAN-TIED INDUCER SECTION AND MULTIPLE LOW PRESSURE TURBINE SECTIONS - A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor. | 08-29-2013 |
20130224003 | GAS TURBINE ENGINE WITH FAN-TIED INDUCER SECTION - A gas turbine engine includes a shaft, a speed change device driven by the shaft, and a fan including a fan rotor driven by the speed change device. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor. | 08-29-2013 |
20130224049 | LIGHTWEIGHT FAN DRIVING TURBINE - A gas turbine engine includes a shaft defining an axis of rotation and a fan driving turbine configured to drive the shaft. The fan driving turbine comprises a plurality of stages that are spaced apart from each other along the axis. Each stage includes a turbine disk comprised of a disk material and a plurality of turbine blades comprised of a blade material. The disk material and the blade material for one of the plurality of stages is selected based on a location of the one stage relative to the other stages of the plurality of stages. | 08-29-2013 |
20130255219 | GEARED TURBOFAN WITH THREE CO-ROTATING TURBINES - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan rotor through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine rotate in the same direction. | 10-03-2013 |
20130255274 | GEARED ARCHITECTURE WITH SPEED CHANGE DEVICE FOR GAS TURBINE ENGINE - A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan. | 10-03-2013 |
20130255275 | GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE - A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction. | 10-03-2013 |
20130259643 | GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO COUNTER-ROTATING, AND THIRD CO-ROTATING WITH THE SECOND TURBINE - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool, with the high speed spool rotating in an opposed direction to the intermediate speed spool. The fan drive turbine rotates in the same direction as the intermediate speed spool. | 10-03-2013 |
20130259650 | GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO CO-ROTATING AND THIRD ROTATING IN AN OPPOSED DIRECTION - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool. | 10-03-2013 |
20130259651 | DIFFERENTIAL GEARED ARCHITECTURE FOR GAS TURBINE ENGINE - A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan, a first compressor section, and a differential gear train that couples the fan and the first compressor section to the first shaft. | 10-03-2013 |
20130259652 | GEARED ARCHITECTURE WITH INDUCER FOR GAS TURBINE ENGINE - A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan. A first compressor section is arranged in an axial flow relationship with the second compressor and the first and second turbines. A geared architecture operatively connects the first shaft and the fan. An inducer operative couples to the gear train. | 10-03-2013 |
20130259653 | GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE - A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction. | 10-03-2013 |
20130259654 | GEARED ARCHITECTURE WITH SPEED CHANGE DEVICE FOR GAS TURBINE ENGINE - A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan. | 10-03-2013 |
20130283819 | GEARED TURBOFAN WITH THREE TURBINES ALL CO-ROTATING - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction. | 10-31-2013 |
20130287545 | GEARED TURBOFAN WITH THREE TURBINES ALL COUNTER-ROTATING - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool and the fan drive turbine configured to rotate in the same first direction. The intermediate speed spool rotates in an opposed, second direction. | 10-31-2013 |
20130287575 | Geared Architecture for High Speed and Small Volume Fan Drive Turbine - A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system. | 10-31-2013 |
20130318998 | GEARED TURBOFAN WITH THREE TURBINES WITH HIGH SPEED FAN DRIVE TURBINE - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor and three turbine sections. A fan drive drives the fan through a gear reduction. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. A second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area. A ratio of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5. | 12-05-2013 |
20130336791 | Geared Architecture for High Speed and Small Volume Fan Drive Turbine - A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system. | 12-19-2013 |
20140020404 | FUNDAMENTAL GEAR SYSTEM ARCHITECTURE - A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system. | 01-23-2014 |
20140102076 | Turbine Section of High Bypass Turbofan - A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170. | 04-17-2014 |
20140130479 | Gas Turbine Engine With Mount for Low Pressure Turbine Section - A gas turbine engine includes a very high speed low-pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for a higher pressure turbine is at a ratio between about 0.5 and about 1.5. In addition, the lower pressure turbine is mounted with a first bearing mounted in a mid-turbine frame, and a second bearing mounted within a turbine exhaust case. | 05-15-2014 |
20140169935 | LIGHTWEIGHT SHROUDED FAN BLADE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis. Each of the plurality of fan blades includes a mid-span shroud and a speed change device in communication with the fan. | 06-19-2014 |
20140174055 | TURBINE SECTION OF HIGH BYPASS TURBOFAN - A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170. | 06-26-2014 |
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 |
20140196472 | GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE - A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine. | 07-17-2014 |
20140196473 | GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE - A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine. | 07-17-2014 |
20140212261 | LIGHTWEIGHT SHROUDED FAN - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan. | 07-31-2014 |
20140216053 | GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION - A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a speed reduction. A sensor senses a speed of rotation of the fan and communicates sensed speed information to a control. The control develops an expected speed for the fan. A problem is identified should the sensed speed be less than the expected speed by more than a predetermined amount. A method is also described. | 08-07-2014 |
20140216056 | HEAT EXCHANGE MODULE FOR A TURBINE ENGINE - A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline. | 08-07-2014 |
20140234079 | Geared Architecture for High Speed and Small Volume Fan Drive Turbine - A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system. | 08-21-2014 |
20140260326 | GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE - A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000° F. and about 1500° F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis. | 09-18-2014 |
20140283501 | ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO - A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (D | 09-25-2014 |
20140286754 | Elongated Geared Turbofan With High Bypass Ratio - A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (D | 09-25-2014 |
20140314541 | TURBOMACHINE THRUST BALANCING SYSTEM - An example turbomachine thrust balancing system includes a member coupled in rotation with a turbine for transferring rotational power therefrom. A load carrying device rotatably supports the member. The load carrying device is configured to counteract substantially all of the thrust load generated by the turbine. | 10-23-2014 |
20150044052 | Geared Turbofan With Fan Blades Designed To Achieve Laminar Flow - A fan blade comprises a main body having an airfoil extending between a leading edge and a trailing edge. The fan blade has at least one of a channel closed by a cover, and an end cap covering at least one of the leading and trailing edges. At least one of a cover and an end cap has a pair of opposed ends. A step is defined extending from at least one of a suction wall and a pressure wall of the airfoil, to an outer surface of the one of a cover and an end cap at one of the opposed ends, and the step being less than or equal to about 0.010 inch (0.0254 centimeter) in dimension. | 02-12-2015 |