Class / Patent application number | Description | Number of patent applications / Date published |
060801000 | Convertible or combined with feature other than combustion products generator or motor | 77 |
20090158748 | Direct induction combustor/generator - A combustor/coil assembly for direct electromagnetic induction from a detonation wave comprises an annular combustor, a magnetic field source and a port. The annular combustor comprises an inner liner and a coaxial outer liner. The outer liner is electrically insulated from the inner liner. The magnetic field source generates a substantially axial magnetic field inside the annular combustor. The port introduces reactants into the annular combustor to form the detonation wave. The detonation wave induces a voltage between the inner liner and the outer liner by forming a current loop between the inner liner and the outer liner. | 06-25-2009 |
20090173081 | METHOD AND APPARATUS TO FACILITATE SUBSTITUTE NATURAL GAS PRODUCTION - A method of producing substitute natural gas (SNG) includes providing a syngas stream that includes at least some carbon dioxide (CO | 07-09-2009 |
20100083668 | Hybrid propulsive engine including at least one independently rotatable compressor stator - One aspect relates to a hybrid propulsive technique, comprising providing a flow of a working fluid through at least a portion of an at least one jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to a torque. The hybrid propulsive technique also comprises rotating an at least one independently rotatable compressor stator at least partially responsive to the converting the at least a portion of the electrical power to the torque. | 04-08-2010 |
20100236257 | GAS TURBINE COMBUSTOR EXIT DUCT AND HP VANE INTERFACE - An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound. | 09-23-2010 |
20100242495 | HYBRID GAS TURBINE ENGINE - ELECTRIC MOTOR/GENERATOR DRIVE SYSTEM - A method of operating a drive system for a load is disclosed. The drive system may have an electric motor/generator and a gas turbine engine. The engine may have a combustor, and main and pilot flow paths via which fuel is supplied to the combustor. The engine may be operable in low and standard emissions modes. A proportion of the fuel that is supplied to the combustor via the pilot flow path may be greater in the standard emissions mode than in the low emissions mode. The method may include determining an engine power requirement of the load, and whether the engine power requirement of the load is sufficiently large to operate the engine in the low emissions mode. Additionally, the method may include operating the electric motor/generator if the engine power requirement of the load is not sufficiently large to operate the engine in the low emissions mode. | 09-30-2010 |
20100293964 | BREATHER DUCT SHIELDING - A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is a clean air outlet slot located downstream of the exhaust port and arranged to expel, in use, a sheet flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port. | 11-25-2010 |
20100300117 | AIRCRAFT WITH DISENGAGEABLE AUXILIARY POWER UNIT COMPONENTS - Several improvements to an aircraft turbine engine and Auxiliary Power Unit (APU) are disclosed, as well as methods of using these improvements in routine and emergency aircraft operations. The improvements comprise the addition of cockpit-controllable clutches that can be used to independently disconnect the engine's integrated drive generator (IDG), engine driven pump (EDP), fuel pump, and oil pump from the engine gearbox. These engine components may then be connected to air turbines by the use of additional clutches and then powered by the turbines. Similar arrangements are provided for the APU components. Cranking pads, attached to various engine and APU components, are disclosed to provide a means for externally powering the components for testing purposes and to assist with engine and APU start. Detailed methods are disclosed to use the new components for routine ground-testing and maintenance and for the enhancement of flight safety, minimization of engine component damage, and extension of engine-out flying range in the case of an emergency in-flight engine shutdown. | 12-02-2010 |
20100307167 | CENTRIFUGAL DE-OILER OF VARIABLE FLOW SECTION - A centrifugal de-oiler of variable flow section, the de-oiler including a hollow shaft that is movable in rotation. The shaft includes at least one air-passing orifice and a piston housed in the shaft so as to subdivide the inside of the shaft into two compartments that are sealed relative to each other. One compartment includes the air-passing orifice(s) being subjected to ambient pressure, and the other compartment is subjected to varying pressure in the air/oil enclosure. The piston is configured to move in translation inside the shaft between two extreme positions under effect of the pressure difference between the two compartments, the extreme position including a first position in which the air-passing orifice(s) is/are disengaged, and a second position in which the air-passing orifice(s) is/are partially obstructed by the piston. | 12-09-2010 |
20110011096 | SYSTEM FOR COOLING COOLING-AIR IN A GAS TURBINE ENGINE - A system for cooling cooling-air in a gas turbine engine, the system having an electricity generating fuel-cell, and an arrangement for receiving water produced by the fuel cell, delivering the water to the engine, and cooling cooling-air inside the engine using the water. | 01-20-2011 |
20110173991 | Turbine Engine - A multiple-fluid, multiple-substance, multiple-phase, multiple-pressure, multiple-temperature, multiple-stage turbine engine. In preferred embodiments, one or more fluids are supplied by passageways in the turbine shaft or supplied by non-shaft passageways, or both, through rotor passageways to multiple-phase, multiple-fluid, multiple-substance nozzles affixed to one or more perimeters, radial surfaces, axial surfaces, and/or curved or slanted surfaces of the turbine rotor assemblies. The multiple perimeters, radial surfaces, axial surfaces, and/or curved or slanted surfaces of the turbine rotor assemblies are preferably configured and located for multiple inlet and exit velocities of the nozzles, multiple inlet and exit pressures of the nozzles, or combinations thereof. The one or more fluids entering the turbine may each be a substance of single phase, or a substance of multiple phases, or a mix of the single-phase and/or multiple-phase conditions for two or more entrance fluids. | 07-21-2011 |
20110277484 | SYSTEM AND METHOD FOR VENTILATING A TURBINE - This ventilation system ( | 11-17-2011 |
20110283712 | THERMOELECTRIC GENERATION FOR A GAS TURBINE - A device for producing electrical power in a gas turbine or the like of an aircraft, the device including a plurality of thermoelectric cells having a face surrounding a hot source. A cold source is constituted by a cold fluid flowing over the other face of the thermoelectric cells. | 11-24-2011 |
20110289935 | Thermal Power Plant, in Particular Solar Thermal Power Plant - A thermal power plant, in particular a solar thermal power plant, includes a gas turbine device, in which a medium circulating in a circuit and heated by thermal energy is conducted through a turbine in order to produce electric energy. The medium is subsequently circulated into a condenser cooled by a cooling device in order to liquefy the medium. The cooling device is designed as a solar-operated cooling device having a closed coolant circuit. | 12-01-2011 |
20120036866 | AUXILIARY POWER UNIT WITH MULTIPLE FUEL SOURCES - A system and method are disclosed for supplying fuel to an auxiliary power unit of an aircraft. The system includes a primary fuel source, a secondary fuel source, and a secondary valve. The primary fuel source is in fluid communication with the auxiliary power unit to provide a primary fuel thereto. Similarly, the secondary fuel source is in fluid communication with the auxiliary power unit to provide a secondary fuel thereto. The secondary valve regulates flow of the secondary fuel from the secondary fuel source to the auxiliary power unit. The method provides a secondary fuel from a secondary fuel source to the auxiliary power unit if an emergency operating condition experienced by the aircraft results from either exhaustion or contamination of a primary fuel. | 02-16-2012 |
20120067063 | ROTOR ASSEMBLY FOR USE IN TURBINE ENGINES AND METHODS FOR ASSEMBLING SAME - A rotor assembly for use with a turbine engine. The rotor assembly includes at least one rotor disk that includes an inner surface that defines a dovetail groove. At least one turbine bucket is coupled to the rotor disk. The turbine bucket includes an airfoil that extends outwardly from a dovetail. The dovetail is inserted at least partially within the dovetail groove. A tang assembly extends from one of the inner surface of the rotor disk and the dovetail. the tang assembly minimizes a rotation of the turbine bucket with respect to the rotor disk. | 03-22-2012 |
20120096870 | COMBINED CYCLE POWER PLANT INCLUDING A CARBON DIOXIDE COLLECTION SYSTEM - A combined cycle power plant includes a compressor section including a compressor inlet and a compressor outlet, and a turbine section operatively connected to the compressor section. The turbine section includes a turbine inlet and a turbine outlet. A heat recovery steam generator (HRSG) is fluidly connected to the turbine outlet. A combustor includes a head end and a combustor discharge. The head end is fluidly connected to the compressor outlet and the combustor discharge is fluidly connected to the turbine inlet. A carbon dioxide collection system is fluidly connected to one of the compressor outlet and the head end of the combustor. The carbon dioxide collection system is configured and disposed to extract a first fluid comprising carbon dioxide and a second fluid from a substantially oxygen free fluid flow passed from the one of the compressor outlet and the head end of the combustor. | 04-26-2012 |
20120102970 | SYSTEMS, METHODS, AND APPARATUS FOR REGENERATING A CATALYTIC MATERIAL - A steam generator coupled in flow communication downstream from a combustion device that produces a flow of exhaust gases includes a heating device configured to heat the exhaust gases that include oxides of nitrogen (NO | 05-03-2012 |
20120117980 | MODULAR PLASMA ASSISTED GASIFICATION SYSTEM - A modular gasification reactor for a plasma assisted gasification reaction system is disclosed for converting fuel, such as, but not limited to, biomass, to syngas to replace petroleum based fuels used in power generation. The system may be a modular system housed within a frame facilitating relatively easy transportation. The system may include a reactor vessel with distinct reaction zones that facilitate greater control and a more efficient system. The system may include a syngas heater channeling syngas collected downstream of the carbon layer support and to the pyrolysis reaction zone. The system may also include a syngas separation chamber configured to produce clean syngas, thereby requiring less filtering. The system may further include an agitator drive assembly that prevents formation of burn channels within the fuel. | 05-17-2012 |
20120167593 | TAPERED BEARINGS - A gearbox support assembly for a turbine engine includes an epicyclic gear arrangement and a first tapered bearing and a second tapered bearing spaced apart from the first tapered bearing. The first tapered bearing and the second tapered bearing support the epicyclic gear arrangement. | 07-05-2012 |
20120234020 | SYSTEMS AND METHODS FOR ASSEMBLING AN EVAPORATIVE COOLER - A method of assembling an evaporative cooler for use with a gas turbine engine system. The method includes coupling a drain pan to a support frame, wherein the drain pan includes a front wall and a back wall. A media support assembly is coupled to the drain pan to form the evaporative cooler. The media support assembly includes a media support wall and a rear flange. The media support wall extends substantially perpendicularly from the drain pan front wall and defines a continuous drainage chamber between the drain pan front wall and the back wall. | 09-20-2012 |
20120304666 | AIRCRAFT CONTROL SYSTEM - The invention relates to a system ( | 12-06-2012 |
20130000323 | DIFFERENTIAL GEAR SYSTEM WITH CARRIER DRIVE - A differential gear system for a gas turbine engine includes an assembly of a ring gear, a sun gear, and a plurality of planet gears, and a planet carrier. The plurality of planet gears are enmeshed between the ring gear and the sun gear. The planet carrier acts as an input to rotatably drive the planet gears, the sun gear, and ring gear of the gas turbine engine. | 01-03-2013 |
20130081405 | GUIDE AND SEALING DEVICE FOR A TURBINE ENGINE, THE DEVICE HAVING A CARBON GASKET AND AN INTEGRATED SMOOTH BEARING - A guide and sealing device a shaft in an orifice in a casing in a turbine engine, the device including a carbon gasket mounted around the shaft including a ring secured to the shaft and having an annular friction face rubbing against a carbon annulus mounted in a support bushing fastened to the casing, the ring presenting a cylindrical wall that is centered and guided in rotation in a cylindrical wall of the support bushing so as to form a smooth bearing for guiding the shaft. | 04-04-2013 |
20130133335 | Power Plant Line Having a Variable-Speed Pump - The invention relates to a power plant line, comprising a steam turbine and/or gas turbine that rotates at a constant speed in order to drive an electric generator; a variable-speed pump for conveying and/or compressing a working medium in order to drive and/or supply the process of the steam turbine and/or the gas turbine or to pump and/or compress an exhaust gas produced in the process supply or in the gas turbine. The invention is characterized in that the variable-speed pump is driven by the steam turbine and/or gas turbine and a speed-controllable gear train is arranged in the driving connection, said gear train having a power split, which comprises a mechanical main branch and a hydrodynamic secondary branch, wherein driving power is branched off from the mechanical main branch via a hydrodynamic coupling or a hydrodynamic converter by means of the hydrodynamic secondary branch and fed back to the mechanical main branch at the output side of the gear train in a variable-speed manner by means of a superimposing gear train. | 05-30-2013 |
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 |
20140007590 | Systems and Methods For Carbon Dioxide Capture In Low Emission Turbine Systems - Systems, methods, and apparatus are provided for generating power in low emission turbine systems and capturing and recovering carbon dioxide from the exhaust. In one or more embodiments, the exhaust is cooled, compressed, and separated to yield a carbon dioxide-containing effluent stream and a nitrogen-containing product stream. | 01-09-2014 |
20140033736 | GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity and a microcircuit in fluid communication with the first cavity. A plunged hole intersects at least a portion of the microcircuit. | 02-06-2014 |
20140123679 | FLEXIBLE HEAT SHIELD FOR A GAS TURBINE ENGINE - A flexible heat shield for a gas turbine engine includes a support layer attached to a ceramic fiber layer. | 05-08-2014 |
20140208770 | COMPONENT HAVING INSERT FOR RECEIVING THREADED FASTENERS - A component formed of a plastic matrix composite material is provided. The component has a metal liner which is fixed in a correspondingly shaped recess formed in the composite material. The liner has a threaded bore into which is screwed an externally threaded, hollow cylindrical, metal insert. The insert has an internal thread for receiving threaded fasteners. The mouth of the bore has engagement formations which engage with the insert to prevent rotation of the insert in the bore, an adjacent part of the insert being plastically deformed to engage with the engagement formations after being screwed into the bore. | 07-31-2014 |
20140290271 | MOUNTING ARRANGEMENT - A rigid electrical raft is provided to a gas turbine engine via a fusible mount arrangement. The rigid electrical raft may be a part of an electrical system of the gas turbine engine, for example a part of the electrical harness. The fusible mount is arranged to break when a predetermined load is applied. The rigid electrical raft may be attached to a fan case of the engine, and the predetermined load may that which results from a fan blade being released from the hub. This ensures that the rigid electrical raft is protected from the load. | 10-02-2014 |
20140305135 | FUEL DRAIN VALVE FOR A TURBINE ENGINE - A valve assembly for an engine, the valve assembly can include a housing; an in-flow port configured for connection with a drain line; a first out-flow port configured for connection with a fuel line; a second out-flow port configured for connection with a disposal line; and a passageway that is rotatable with a handle, the passageway being operable to redirect a flow of a fluid between the fuel line and the disposal line. The handle is configured to impede an attachment of the fluid source to a water wash connection when the passageway is in a position to direct the flow of the fluid from the drain line to the fuel line. | 10-16-2014 |
20140305136 | MOUNTING ARRANGEMENT - A gas turbine engine is provided that has a rigid dressing raft mounted to a rigid part of the gas turbine engine. The rigid dressing raft includes at least a part of a component or system of the gas turbine engine. For example, the rigid dressing raft may have electrical conductors embedded therein that are a part of the electrical system of the gas turbine engine. | 10-16-2014 |
20140325994 | ELECTRICAL CONNECTORS - An electrical raft is provided comprising a rigid material having multiple electrical conductors embedded therein. An electrical connector is provided to the raft that has a back-shell which is embedded in the rigid material and which joins to a connector body to enclose a first end of a housing of the connector body. The housing also has a second end at which electrical contacts are provided for connection to another component. The connector body is detachable from the back-shell to electrically disconnect it from the embedded electrical conductors and allow removal of the connector body from the electrical raft. In this way, the connector body may be readily removed, for example for upgrade or repair, whilst retaining a robust and reliable connection. | 11-06-2014 |
20140325995 | COMPOSITE STRUCTURE - A composite structure is provided. The structure is formed of rigid composite material in which non-metallic continuous fibres reinforce a polymer matrix. The continuous fibres are electrically conductive. The structure has electrodes electrically connected to the continuous fibres. The composite material contains one or more insulating barriers which electrically divide the structure so that a first portion of the material in electrical contact with one of the electrodes can be held at a different electrical potential to a second portion of the material in electrical contact with the other electrode. In use, an electrical unit can be provided to electrically bridge the first and second portions of the material such that electrical signals can be transmitted between the electrodes and the electrical unit via the continuous fibres. | 11-06-2014 |
20150033760 | Solar Assisted Gas Turbine System - It is an object of the present invention to provide a solar assisted gas turbine system that has a largely reduced number of heat collectors and a reduced installation area required for installation of the heat collectors. The solar assisted gas turbine system of the invention includes a gas turbine unit having a compressor for compressing air, a combustor for putting the air compressed by the compressor and a fuel into combustion, and a turbine driven by a combustion gas generated in the combustor; a heat collector for collecting solar heat and forming high-pressure hot water; a heat storage tank for storing the heating medium raised in temperature; a heat-exchanger for performing heat exchange between the heating medium and water to form hot water; and an atomizer by which the hot water formed by the heat-exchanger is sprayed into the air to be taken into the compressor. | 02-05-2015 |
20150135727 | AUTOMATED WATER WASH SYSTEM FOR A GAS TURBINE ENGINE - The present application and the resultant patent provide a gas turbine engine system. The gas turbine engine system may include a gas turbine engine, a water wash system, and a system controller. The gas turbine engine may include a compressor, a combustor in communication with the compressor, and a turbine in communication with the combustor. The water wash system may be in communication with the gas turbine engine and configured to remove contaminants therefrom. The water wash system may include a number of valves configured to control flows through the water wash system, and a number of sensors configured to measure operating parameters of the water wash system. The system controller may be in communication with the valves and the sensors and operable to automatically control the valves upon receiving operating parameter signals from the sensors in order to perform a wash of the gas turbine engine. | 05-21-2015 |
20150345386 | POWER GENERATION SYSTEM - This power generation system is provided with: a gas turbine ( | 12-03-2015 |
20150354462 | OFF-LINE WASH SYSTEMS AND METHODS FOR A GAS TURBINE ENGINE - The present application and the resultant patent provide a wash system for a gas turbine engine. The wash system may include a water source containing a volume of water therein, and a surface filming agent source containing a volume of a surface filming agent therein. The wash system also may include a mixing chamber in fluid communication with the water source and the surface filming agent source, wherein the mixing chamber is configured to mix the water and the surface filming agent therein to produce a film-forming mixture. The wash system further may include a number of supply lines in fluid communication with the mixing chamber, wherein the supply lines are configured to direct the film-forming mixture into the gas turbine engine. The present application and the resultant patent also provide a related method of washing a gas turbine engine to remove contaminants therefrom. | 12-10-2015 |
20160010567 | FUEL-AIR RATIO CONTROL OF GAS TURBINE ENGINES | 01-14-2016 |
20160076446 | AIRCRAFT HYBRID ENGINE - A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator. | 03-17-2016 |
20160115874 | LINER GROMMET ASSEMBLY - A base for a grommet assembly of a combustion chamber is disclosed. The base includes a base body and a cooling extension. The base body includes a first body portion having a first hollow cylinder sector shape and a second body portion having a second hollow cylinder sector shape. The first portion is thicker than the second portion. The cooling extension includes a cylindrical portion with a third hollow cylinder sector shape and an annular portion. The cylindrical portion extends axially from the base body. The annular portion extends radially from the cylindrical portion distal to the base body. | 04-28-2016 |
20160201605 | ENGINE | 07-14-2016 |
20170234315 | GAS TURBINE BLOWER/PUMP | 08-17-2017 |
060802000 | Motor driven accessory | 22 |
20090000308 | Generator with separate oil system for improved nacelle performance - An electrical generator assembly for use in a gas turbine engine, which assembly includes an electrical motor configured to connect to an accessory gearbox arranged radially outward of a main axis of the gas turbine engine and inside a nacelle, and fluid connections between the electrical motor and a generator oil system. The generator oil system is offset from the electrical motor such that the generator oil system is not located radially outward of the electrical motor and inside the nacelle. | 01-01-2009 |
20090139243 | GAS TURBINE ENGINE WITH PYLON MOUNTED ACCESSORY DRIVE - A gas turbine engine includes an accessory gearbox within an engine pylori. The accessory components may be mounted within the engine pylori to save weight and space within the core nacelle as well as provide a relatively lower temperature operating environment. | 06-04-2009 |
20090165464 | JET ENGINE WITH DETACHABLY ARRANGED GENERATOR UNIT - The present technology generally relates to jet engines, in particular for an aircraft, having at least one turbine shaft on which at least one compressor and a turbine are arranged, and a housing extends over the lateral surfaces of the jet engine, wherein furthermore at least one electrical generator unit for generating electricity is arranged on at least one turbine shaft, wherein the electrical generator unit has a locating plate and a generator, wherein the generator unit is detachably mounted on the engine-side locating plate. Therefore, a jet engine having a generator unit is provided which permits simple installation, removal and servicing of the generator unit in or out of the jet engine. | 07-02-2009 |
20100083669 | Hybrid propulsive engine including at least one independently rotatable propeller/fan - One aspect relates to a hybrid propulsive technique comprising providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further comprises rotating an at least one independently rotatable propeller/fan of at least one rotatable propeller/fan assembly at least partially responsive to the converting the at least a portion of the electrical power to torque, wherein the rotating of the at least one independently rotatable propeller/fan of the at least one rotatable propeller/fan assembly is arranged to produce at least some second thrust. | 04-08-2010 |
20100186418 | TURBINE ENGINE WITH A POWER TURBINE EQUIPPED WITH AN ELECTRIC POWER GENERATOR CENTERED ON THE AXIS OF THE TURBINE ENGINE - The present invention relates to a turbine engine ( | 07-29-2010 |
20100242496 | GAS TURBINE ENGINE WITH STACKED ACCESSORY COMPONENTS - An engine accessory system for a gas turbine engine includes a first accessory component defined along an accessory axis and a second accessory component mounted to the first accessory component along the accessory axis. | 09-30-2010 |
20110167835 | TURBINE ENGINE WITH A POWER TURBINE EQUIPPED WITH AN ELECTRIC POWER GENERATOR - The present invention relates to a turbine engine for aircraft comprising a gas generator as well as to a receiver driven by a power turbine ( | 07-14-2011 |
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 |
20120079832 | DEVICE AND METHOD FOR DETECTING A FAULT IN A LOW-PRESSURE FUEL PUMP OF A TURBOJET AND TURBOJET INCLUDING ONE SUCH DEVICE - A device for detecting a fault in a low-pressure fuel pump of a turbojet. The pump is driven by an accessory gearbox including a gear for mechanically driving the accessories. The device measures the vibration frequencies of the accessory gearbox and detects, from among the frequencies, at least one vibration frequency of the low-pressure fuel pump. The device allows a fault in the low-pressure fuel pump to be detected as soon as it occurs. | 04-05-2012 |
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 |
20120159966 | GEARBOX ASSEMBLY - An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct. | 06-28-2012 |
20130074519 | AUXILIARY POWER UNIT INLET DOOR POSITION CONTROL SYSTEM AND METHOD - Methods and apparatus are provided for controlling an auxiliary power unit (APU) inlet door. A plurality of APU operational parameters and a plurality of aircraft operational parameters are sensed. The APU operational parameters and the aircraft operational parameters are processed to determine a minimum APU inlet door position that will maintain APU turbine inlet temperature at a predetermined value. The APU inlet door is then moved to the determined minimum APU inlet door position. | 03-28-2013 |
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 |
20130098067 | CONSTANT SPEED TRANSMISSION FOR GAS TURBINE ENGINE - A gas turbine engine includes a constant speed transmission driven by a spool. | 04-25-2013 |
20130125561 | GEARED TURBOFAN WITH DISTRIBUTED ACCESSORY GEARBOXES - A disclosed gas turbine engine includes a core engine defined about an engine centerline axis, the core engine including a compressor section driven through a shaft by a turbine section. A core nacelle surrounds the core engine and a fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path for a bypass airflow. A fan section disposed within the fan nacelle is driven by the turbine section of the core engine through a geared architecture. An engine pylon supports the core nacelle and the fan nacelle. A towershaft is driven by the shaft of the core engine and drives a generator mounted within the core nacelle. The generator powers an electric motor mounted within the engine pylon. The electric motor drives a plurality of accessory components that are also mounted within the engine pylon. | 05-23-2013 |
20130133336 | SUPPORT FOR ELECTRIC MACHINE IN A TURBINE ENGINE - Devices and methods for supporting an accessory ( | 05-30-2013 |
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 |
20130180262 | GAS TURBINE ENGINE ACCESSORY GEARBOX - An accessory gearbox for a gas turbine engine has a main gearbox housing for receiving a plurality of gears to drive a plurality of accessories. An input shaft has a first bevel gear at an outer end, and extends inwardly to transmit rotation to the plurality of gears. A tower shaft has a second bevel gear engaging the first bevel gear to in turn drive the input shaft. A tower shaft houses is fixed to the main gearbox housing. A method of removing a tower shaft is also disclosed. | 07-18-2013 |
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 |
20130319003 | AUXILIARY POWER UNIT MOUNT WITH FIRE RESISTANT SHIELDING - An auxiliary power unit has a gas turbine engine, a generator, and a gear box. A mount bracket is mechanically attached to the gear box. The bracket is for connecting to a plurality of struts. The struts are for connecting to an aircraft housing. A shield box is formed of a flame resistant rigid material. The shield box encloses the mount bracket to provide flame protection to the mechanical attachment. | 12-05-2013 |
20140116064 | VENTILATION OF AN ACCESSORY GEAR BOX, AND TURBOJET ENGINE COMPRISING SUCH A GEAR BOX - An accessory gear box configured to be mounted on a fan casing of a turbojet engine, including: an input shaft; a plurality of accessory drive shafts; and a compartment forming an interface with an accessory arranged on the housing of the accessory gear box at a site of the accessory, the interface compartment including an inlet and an outlet configured to allow air to circulate inside the compartment, to insulate the accessory gear box from heat generated by the accessories. | 05-01-2014 |
060803000 | Motor condition sensing feature | 12 |
20110056214 | SMART WIRELESS ENGINE SENSOR - Sensors are mounted to an engine to detect engine conditions and send information to an engine controller or other engine component through a wireless connection. Ports are located on the engine controller. An antenna assembly is plugged into one of the ports and wirelessly receives the signal from the sensor. Another antenna assembly transmits a signal from the engine controller to an external component. A processor within the antenna assemblies monitors and adjusts the signals to correct for signal interference. | 03-10-2011 |
20120167594 | Bypass Monitor for Fuel Supply System - A method for monitoring a fuel supply system for a turbine engine, the fuel supply system comprising a fuel pump and a pressure regulation valve configured to receive fuel from an outlet of the fuel pump includes determining by a bypass monitor an amount of bypass flow in a bypass path located between the pressure regulation valve and an inlet of the fuel pump; determining an amount of leakage flow in the fuel supply system by the bypass monitor based on the bypass flow; and determining whether the leakage flow exceeds a predetermined threshold by the bypass monitor, and in the event the leakage flow exceeds the predetermined threshold, indicating a need for maintenance of the fuel supply system. | 07-05-2012 |
20130008180 | METHOD AND APPARATUS FOR DISTRIBUTED CLEFT AND LIBERATED TILE DETECTION ACHIEVING FULL COVERAGE OF THE TURBINE COMBUSTION CHAMBER - A component sensing system for monitoring the condition of ceramic tiles in a combustion chamber of a gas turbine engine. The sensing system includes an optical fiber that is mounted to the component being monitored, for example, the ceramic tiles in the gas turbine combustion chamber. The optical fiber can be formed in any suitable orientation or configuration, such as a meandering or serpentine orientation. The fiber is optically coupled to a Brillouin signal analyzer that provides an optical pulse to the sensing section of the fiber and detects Brillouin backscattering from the fiber as the pulse travels along the fiber. The frequency of the Brillouin backscattering signal is monitored relative to the distance along the sensing section of the fiber. A rise in temperature at a location of the fiber shows up in the analyzer as an increase in frequency of the backscattered signal. | 01-10-2013 |
20130167554 | TEMPERATURE SENSING DEVICE AND METHOD OF ASSEMBLING THE SAME - A method of assembling a temperature sensing device for a gas turbine engine is provided. The method includes providing a temperature sensor and providing a housing configured to envelop the temperature sensor. The method further includes mounting the temperature sensor within the housing such that a portion of the temperature sensor is disposed outside of the housing and such that the housing is configured to receive a flow of cooling air. | 07-04-2013 |
20130192259 | TURBINE ENGINE MONITORING SYSTEM - A turbine engine system includes a turbine engine shaft, a first rotor, a second rotor and an engine monitoring system. The shaft includes a shaft bore formed by a shaft wall. The shaft bore extends along an axial centerline through the shaft between a first shaft end and a second shaft end. The first rotor is connected to the shaft at the first shaft end, and the second rotor is connected to the shaft at the second shaft end. The engine monitoring system includes a sensor connected to the second rotor, a transmitter arranged at the first shaft end, and a plurality of conduit assemblies. Each conduit assembly includes a conduit that extends axially within the shaft bore and is connected to the shaft wall. A first of the conduit assemblies also includes a wire that extends through a respective conduit and connects the sensor and the transmitter. | 08-01-2013 |
20130199206 | SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE - A gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan about an engine central axis, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled to drive a first spool. The first spool is coupled at a first axial position to a compressor hub that is coupled to drive the first compressor. The first spool is also coupled at a second, different axial position to a fan drive input shaft that is coupled to drive the fan drive gear system. The turbine section also includes a second turbine coupled through a second spool to drive the second compressor. A sensor probe is operable to determine a rotational speed of the first spool. The sensor probe is located at a third axial position that is axially forward of the first axial position and axially aft of the second axial position. | 08-08-2013 |
20130340443 | Plug Assembly for Borescope Port Cooling - A removable plug assembly modified for port cooling plugs a borescope port but allows controlled leakage to cool surfaces adjacent the port below oxidation limits. The plug assembly has a plunger and plug wherein the plug includes a plurality of flow recesses allowing bypass air to cool the surface having the port, as well as the borescope plug. | 12-26-2013 |
20140033737 | METHOD AND SYSTEM FOR GAS TEMPERATURE MEASUREMENT - A temperature measurement system includes at least one filament configured to emit thermal radiation in a relatively broad and substantially continuous wavelength band that is at least partially representative of a temperature of the at least one filament. The system also includes an optical system configured to receive at least a portion of the thermal radiation emitted from the filament. The optical system includes a wavelength splitting device configured to split the emitted thermal radiation into at least one relatively narrow wavelength band of thermal radiation. The optical system also includes a detector array configured to receive the at least one relatively narrow wavelength band of thermal radiation and to generate electrical signals at least partially representative of the received thermal radiation. The temperature measurement system further includes a controller communicatively coupled to the detector array. The controller is configured to transform the generated electrical signals to a temperature indication using a predetermined conversion module. | 02-06-2014 |
20140053574 | SYSTEM FOR REMOTE VIBRATION DETECTION ON COMBUSTOR BASKET AND TRANSITION IN GAS TURBINES - A gas turbine combustor vibration sensing system includes a non-contact reflective optical vibration sensor adapted for reflecting photons off of a component within the combustor with a photon source and receiving reflected photons with a photon detector. Exemplary combustor internal components include the combustor basket or transition. A vibration analyzer is coupled to the vibration sensor, for correlating photons received by the detector with vibration characteristics of the component. Vibration characteristics in turn can be correlated with combustion characteristics, including by way of example flame front position and flameout conditions. Vibration characteristic information may be used as an operational parameter by a turbine monitoring system to modify operation of a gas turbine. | 02-27-2014 |
20140260323 | GAS TURBINE ENGINE AND ACTIVE BALANCING SYSTEM - The present disclosure provides, in one embodiment, a unique gas turbine engine. Other embodiments include unique gas turbine engines, and unique active balancing systems; as well as apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and active balancing systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 09-18-2014 |
20150040581 | BORESCOPE ASSEMBLY AND METHOD OF INSTALLING BORESCOPE PLUGS - A borescope assembly includes a first borescope plug comprising a first perimeter geometry portion. Also included is a second borescope plug comprising a second perimeter geometry portion distinct from the first perimeter geometry portion. Further included is a first borescope hole comprising a first hole geometry portion corresponding to the first perimeter geometry portion of the first borescope plug. Yet further included is a second borescope hole comprising a second hole geometry portion corresponding to the second perimeter geometry portion of the second borescope plug. | 02-12-2015 |
20150300251 | IR SENSOR/SYSTEM FOR DETECTION OF HEATING ASSOCIATED WITH CRACK PROPAGATION DURING OPERATION OF ROTATING EQUIPMENT - A thermal imaging system that detects the growth of cracks in a structural element, where the system has particular application for detecting the growth of cracks and similar defects in a turbine blade. The thermal imaging system includes at least one infrared (IR) fiber optic cable where a sensing end of the fiber optic cable is positioned in close proximity to a location where a crack in the structural element may occur. Infrared emissions generated as a result of crack growth are collected by the IR fiber cable and transmitted by the cable to an infrared monitoring device. The amount of heat that is detected provides an indication of whether the crack is growing, and if so, at what rate. | 10-22-2015 |