Class / Patent application number | Description | Number of patent applications / Date published |
060791000 | Re-expansion | 67 |
20100293963 | Two-Shaft Gas Turbine - On a two-shaft gas turbine, on at least one of an inner peripheral side or an outer peripheral side of a main flow passage, an outlet of a high-pressure turbine is lower than an inlet of a low-pressure turbine, an outer periphery of a flow channel that connects the outlet of the high-pressure turbine and the inlet of the low-pressure turbine includes a first casing shroud that is supported by a casing and located on an outer peripheral side of a final-stage rotor vane of the high-pressure turbine, and an initial-stage stator vane of the low-pressure turbine, and a connection position of the first casing shroud and the initial-stage stator vane of the low-pressure turbine is closer to the inlet of the initial-stage stator vane of the low-pressure turbine than the outlet of the final-stage rotor vane of the high-pressure turbine. | 11-25-2010 |
20110167833 | METHOD FOR STARTING PREMIXED COMBUSTION IN COMBUSTOR FOR TWO-SHAFT GAS TURBINE - A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out. | 07-14-2011 |
20120055169 | TURBINE ENGINE COMPRISING AN EXHAUST-GAS GUIDE CONE WITH A SOUND SUPPRESSOR - A gas turbine engine, in which gases flow upstream to downstream, including a combustion chamber, a high-pressure turbine placed downstream from the combustion chamber, arranged so as to receive combustion gases from the combustion chamber, a free turbine, and an exhaust-gas guide cone attached to the free turbine downstream from the free turbine, the turbine engine emitting sound waves during operation. The guide cone includes a sound suppressor, for example with a Helmholtz resonator structure, with a resonant cavity and a resonator neck in communication with an opening, arranged so as to suppress the sound waves emitted by the turbine engine. | 03-08-2012 |
20120272659 | REHEAT BURNER INJECTION SYSTEM - The disclosure relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body, and with reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions. | 11-01-2012 |
20130025293 | TEMPERATURE MIXING ENHANCEMENT WITH LOCALLY CO-SWIRLING QUENCH JET PATTERN FOR GAS TURBINE ENGINE COMBUSTOR - A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines. | 01-31-2013 |
20140109591 | DAMPER ARRANGEMENT FOR REDUCING COMBUSTION-CHAMBER PULSATION - The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor. | 04-24-2014 |
20140318147 | LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE - A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed. | 10-30-2014 |
20150114001 | SEALING COMPONENT FOR REDUCING SECONDARY AIRFLOW IN A TURBINE SYSTEM - A sealing component for reducing secondary airflow in a turbine system includes a first end segment configured to be disposed between, and retained in a radial direction by, a first land on a first rotor disk and a first turbine bucket platform operatively coupled to the first rotor disk. Also included is a second end segment configured to be disposed between, and retained in a radial direction by, a second land on a second rotor disk and a second turbine bucket platform operatively coupled to the second rotor disk. Further included is a main body portion extending axially from the first end segment to the second end segment. | 04-30-2015 |
20150135725 | GAS-TURBINE ENGINE - This invention relates to gas turbine engines of continuous combustion in a high speed gas flow through an open circuit in high heating value gas turbine fuels. It may be used in transportation facilities, such as aviation and power plants, and also as a drive in gas compressor units. | 05-21-2015 |
20150330301 | GAS TURBINE ENGINE WITH VARIABLE SPEED TURBINES - Embodiments of the present invention include unique gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 11-19-2015 |
20150377122 | TURBINE SECTION OF HIGH BYPASS TURBOFAN - A turbofan engine includes an engine case, a gaspath through the engine case, a fan having an array of fan blades, a compressor in fluid communication with the fan, a combustor in fluid communication with the compressor, and a turbine in fluid communication with the combustor. The turbine has a fan drive turbine section having 3 to 6 blade stages. A speed reduction mechanism couples the fan drive turbine section to the fan. A ratio of maximum gaspath radius along the low pressure turbine section to maximum radius of the fan blades is less than about 0.55. A bypass area ratio is greater than about 6.0. A ratio of a fan drive turbine section airfoil count to the bypass area ratio is less than about 170 and a second turbine section. | 12-31-2015 |
20160047303 | POWER TRAIN ARCHITECTURES WITH MONO-TYPE LOW-LOSS BEARINGS AND LOW-DENSITY MATERIALS - Power train architectures with mono-type low-loss bearings and low-density materials are disclosed. The gas turbine used in these architectures can include a compressor section, a turbine section, and a combustor section. A generator, coupled to the rotor shaft, is driven by the turbine section. The compressor section, the turbine section, and the generator include rotating components, at least one of the rotating components in one of the compressor section, the turbine section, and the generator including a low-density material. Bearings support the rotor shaft within the compressor section, the turbine section and the generator, wherein at least one of the bearings is a mono-type low-loss bearing. | 02-18-2016 |
060792000 | Multi-spool turbocompressor | 33 |
20090007569 | HIGH TO LOW PRESSURE SPOOL SUMMING GEARBOX FOR ACCESSORY POWER EXTRACTION AND ELECTRIC START - A turbine engine includes low and high pressure spools. A high power take-off shaft is coupled to the high spool. An auxiliary component, such as a generator, is configured to be driven by the high power take-off shaft at a first speed. The low spool, in part, drives the auxiliary component, for example, by interconnecting the high power take-off shaft to a lower power take-off shaft through a speed summing gearbox. The gearbox drives the auxiliary component and increases the rotational speed of the auxiliary component from the first speed to the second speed. The low power take-off shaft also drives another generator, in one example. The turbine engine can be started by the low pressure generator, for example, in response to a command from a controller, which transforms the generator into a starter motor. | 01-08-2009 |
20090031732 | Low speed rotor shaft for a small twin spool gas turbine engine - An inner rotor shaft for use in a small twin spool gas turbine engine, the inner rotor shaft having a hollow middle section formed of a smaller diameter hollow section on a compressor end and a larger diameter hollow section on the turbine end of the shaft. Solid shaft end extend from the hollow section to form a forward solid shaft end to secure the fan rotor disk and an aft solid shaft end to secure the turbine rotor disk. A parabolic shaped transition section joins the forward shaft end to the smaller diameter hollow section, and a conical shaped transition section joins the aft shaft end to the larger diameter hollow section. A conical shaped transition piece joins the two hollow sections together to form an inner rotor shaft that can fit within a minimal space between the compressor rotor disk and the annular combustor assembly of the engine. The conical shaped transition section on the turbine end is so shaped in order to fit within a space formed inside the high pressure turbine rotor disk of the engine in order to minimize the axial spacing between the bearings that support the inner rotor shaft and raise the critical speed of the shaft to a safe level above the operating speed of the engine in order to make such a small twin spool gas turbine engine possible. | 02-05-2009 |
20090064683 | POWER TAKE-OFF SYSTEM AND GAS TURBINE ENGINE ASSEMBLY INCLUDING SAME - A power take-off system for a gas turbine engine includes a starter coupled to a second spool, and a clutch assembly coupled between the starter and a first spool, the clutch assembly configured to couple the first spool to the starter when starting the gas turbine engine assembly. A method of assembling a gas turbine engine assembly that includes the power take-off system, and a gas turbine engine assembly including the power take-off system are also described. | 03-12-2009 |
20090145136 | TIP TURBINE ENGINE WITH MULTIPLE FAN AND TURBINE STAGES - A tip turbine engine ( | 06-11-2009 |
20090205341 | GAS TURBINE ENGINE WITH TWIN TOWERSHAFT ACCESSORY GEARBOX - A gas turbine engine includes a high towershaft driven by a high pressure spool and a low towershaft driven by a low pressure spool. | 08-20-2009 |
20090288421 | TURBINE DRIVE SYSTEM WITH LOCK-UP CLUTCH AND METHOD - A pneumatically driven turbine drive system is coupled to a gas turbine engine that includes low and high pressure compressors, low and high pressure turbines, a lock-up clutch, and at least one engine accessory driven by the high pressure compressor. The pneumatically driven turbine drive system selectively bleeds air discharged from the high pressure compressor and supplies it to an air turbine that is coupled to the at least one engine accessory. Thus, the system selectively reduces the power extracted from the high pressure compressor and is capable of supplying power back to the engine core. This, coupled with the bleed air that is diverted from the high pressure turbine and the low pressure turbine, allows the high pressure spool and the low pressure spool to run at lower speeds when high engine thrust is not needed or desired, but when the at least one engine accessory is still needed. | 11-26-2009 |
20090314005 | PISTON ENGINE SYSTEMS AND METHODS - The method for operating a piston engine system that includes modifying valve timing such that the gas displaced from the piston chamber is at a pressure and temperature nearly equivalent to the temperature and pressure at the end of the combustion stroke rather than being throttled as is the case for traditionally valve timings. When the high temperature and pressure gas enters an exhaust channel, thermally isolating means may line the exhaust channel such that the high temperature of the exhaust gas is maintained. A heat exchanger and an expander may be placed along the exhaust channel such that the high temperature and pressure of the exhaust gas are captured for useful work. | 12-24-2009 |
20100005810 | POWER TRANSMISSION AMONG SHAFTS IN A TURBINE ENGINE - A method of transmitting power among a plurality of shafts in a turbine engine is disclosed herein as well as a turbine engine for practicing the method. The turbine engine includes a compressor section having a low pressure portion and a high pressure portion. The turbine engine also includes a turbine section spaced from the compressor section along a centerline axis. The turbine section includes a low pressure portion and a high pressure portion. The turbine engine also includes a low pressure shaft extending between the low pressure portion of the compressor section and the low pressure portion of the turbine section. The turbine engine also includes a high pressure shaft extending between the high pressure portion of the compressor section and the high pressure portion of the turbine section. The turbine engine also includes a tower shaft operably engaged with both of the low pressure shaft and the high pressure shaft. The tower shaft can impart initial rotation to the high pressure shaft and the low pressure shaft can transmit power through the tower shaft after initial rotation has been imparted to the high pressure shaft. | 01-14-2010 |
20100154435 | TURBINE ENGINE HAVING TWO OFF-AXIS SPOOLS WITH VALVING-ENABLED MODULATION BETWEEN HIGH AND LOW POWER MODES - A turbine engine particularly suited for VTOL aircraft is disclosed. According to various embodiments, the core of the turbine engine includes two spools—a low pressure (LP) spool and a high pressure (HP) spool—where the LP spool is independently mounted remote to the HP spool. The engine may be modulated for operation by a modulation diverter valve assembly and through the fuel flow to the engine. The power output from the engine can be modulated from high levels to low levels and vice versa through control of the air flow through the engine using the modulation diverter valve assembly. In lift mode operation both the LP and HP spools may be operational, while during the forward flight cruise mode of operation the HP spool is operational and the LP spool may or may not be operational depending upon the power required for the flight condition. For HP spool only operation, the LP spool may be shut down using the modulation diverter valve assembly and an inlet flow diverter valve assembly. The convertible configuration may be achieved by the diverter valving-enabled modulation of the engine airflow direction to produce a characteristic for one embodiment having shaft power output for the vertical lift mode to propulsive thrust output for forward flight mode. | 06-24-2010 |
20100192595 | GAS TURBINE ENGINE ASSEMBLY AND METHODS OF ASSEMBLING SAME - A turbine engine assembly includes, a core gas turbine engine, a first low-pressure turbine section in serial flow communication with the core gas turbine engine, the first low-pressure turbine section configured to rotate in a first rotational direction, a first gear assembly coupled to the first low-pressure turbine section, a second low-pressure turbine section coupled to the gear assembly, the second low-pressure turbine section configured to rotate in a second rotational direction, and a fan assembly coupled to the second low-pressure turbine section. | 08-05-2010 |
20100229568 | GAS TURBINE ENGINE - A gas turbine engine is disclosed having a compressor, a combustion chamber downstream of the compressor, and a turbine downstream of the combustion chamber. The compressor includes a first group of compressor blade wheels and a second group of compressor blade wheels downstream of the first group of compressor blade wheels and rotating in an opposite direction such that a deviation of a performance, defined as air mass flow per second between the first group of compressor blade wheels and the second group of compressor blade wheels, is minimized, and a detachment of the air mass flow from blades of a first blade wheel of the second group of compressor blade wheels is substantially eliminated. A bypass enables the air mass flow flowing from the first group of the compressor blade wheels to substantially serve all of the second group of compressor blade wheels substantially simultaneously. | 09-16-2010 |
20110056213 | SPOOL SUPPORT STRUCTURE FOR A MULTI-SPOOL GAS TURBINE ENGINE - A gas turbine engine is provided that includes a low pressure spool, a high pressure spool, a stationary support frame, and at least one support arch. The low pressure spool extends between a low pressure compressor and a low pressure turbine. The high pressure spool extends between a high pressure compressor and a high pressure turbine. The spools are rotatable about a center axis of the engine. The support arch has a stationary support mount disposed between a low spool mount and a high spool mount. The support arch is disposed relative to the spools and the stationary support frame so that a load from each spool caused by the rotation of that spool can be transferred to the stationary support frame through the support arch. The support arch can freely rotate about the center axis of the engine relative to the spools and the stationary structural frame. | 03-10-2011 |
20120017603 | DOUBLE-BODY GAS TURBINE ENGINE PROVIDED WITH AN INTER-SHAFT BEARING - A double-body gas turbine engine, including a low-pressure body LP and a high-pressure body HP, rotatably mounted about a single shaft in a stationary casing, the low-pressure body LP including a compressor and a turbine connected by a low-pressure shaft LP. The low-pressure shaft LP is supported by an upstream LP bearing, a first downstream LP bearing, and an additional downstream LP bearing by the stationary casing, the high-pressure body being supported by an upstream HP bearing and a downstream HP bearing which is an inter-shaft bearing including an inner track rigidly connected to the HP turbine rotor and an outer track rigidly connected to the LP shaft. | 01-26-2012 |
20120167591 | TURBOSHAFT ENGINE WITH PARALLEL SHAFTS - A free-turbine turboshaft engine including a gas generator including at least one compressor supplied with air, a combustion chamber receiving the compressed air at the output of the compressor, and at least one generator turbine mechanically connected to the compressor by a drive shaft and driven by gases from combustion of fuel carried out in the combustion chamber, and including a free turbine supplied by the gases from the combustion after passing through the generator turbine and which drives a power shaft positioned non-coaxially relative to the drive shaft of the gas generator and supplying the power of the turboshaft engine via a reduction gear. The combustion chamber is a substantially cylindrical or frusto-conical chamber, coaxial with the axis of the generator turbine, and includes a single injector. | 07-05-2012 |
20120192570 | PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM - A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed. | 08-02-2012 |
20120234017 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion. | 09-20-2012 |
20120279231 | REGENERATIVE BRAKING FOR GAS TURBINE SYSTEMS - The present invention is directed to an energy storage system comprised of a heat block having a relatively high specific energy capacity. The heat block can be used, for example, with a regenerative braking system for gas turbine powered vehicles to improve fuel efficiency. | 11-08-2012 |
20130000322 | COUNTER-ROTATING TURBOMACHINERY - A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls. | 01-03-2013 |
20130111923 | GAS TURBINE ENGINE COMPONENT AXIS CONFIGURATIONS - A method is disclosed to enable the efficient physical packaging of gas turbine engine components to optimize power density, more readily integrate with other equipment and facilitate maintenance. The method illustrates dense packaging of turbomachinery by close-coupling of components, and rotation of various engine components with respect to engines and/or other engine components, and reversal of spool shaft rotational direction to suit the application. Engines can be dense-packed because of a number of features of the basic engine including the use of compact centrifugal compressors and radial inlet turbine assemblies, the close coupling of turbomachinery, the ability to rotate key components to facilitate ducting and preferred placement of other components, the ability to control spool shaft rotational direction and full power operation at high overall pressure ratios. | 05-09-2013 |
20130239584 | CONSTANT-SPEED PUMP SYSTEM FOR ENGINE THERMAL MANAGEMENT SYSTEM AOC REDUCTION AND ENVIRONMENTAL CONTROL SYSTEM LOSS ELIMINATION - A gas turbine engine has a spool, a towershaft connected to the spool, an impeller pump, and a speed control pump connected to the towershaft and to the impeller pump for driving the impeller pump at a constant speed. | 09-19-2013 |
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 |
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 |
20130318999 | GAS TURBINE ENGINE WITH A COUNTER ROTATING FAN - An exemplary gas turbine engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The fan includes a first plurality of fan blades supported on a first fan support and a second plurality of fan blades supported on a second fan support. The first and second fan supports are rotatable about a fan axis independently of each other. A geared architecture includes at least one gear driven by the turbine section for rotating about a gear axis that is transverse to the fan axis. The gear drives the fan supports for rotating the respective pluralities of fan blades in opposite directions. | 12-05-2013 |
20140230452 | PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM - In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations. | 08-21-2014 |
20150096303 | 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. | 04-09-2015 |
20150114002 | GEARED TURBOFAN ENGINE WITH A HIGH RATIO OF THRUST TO TURBINE VOLUME - 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. | 04-30-2015 |
20150345383 | Gas Turbine Engine Core Utilized in Both Commercial and Military Engines - A method of manufacturing a military engine includes the steps of designing a commercial engine core, including a combustor, a high pressure compressor driven by a high pressure turbine, and a low pressure turbine designed to drive a low pressure compressor, and a fan through a gear reduction. A high speed fan is attached to the low pressure turbine, such that the combustor, high pressure compressor, low and high pressure turbines from an engine designed for commercial purposes is utilized for military purposes. A gas turbine engine is also disclosed. | 12-03-2015 |
20150354463 | Two Spool Gas Generator with Mount Ring - A gas turbine engine has a first shaft including a first turbine rotor, and a second shaft including a second turbine rotor disposed downstream of the first turbine rotor. A third shaft includes a propulsor turbine positioned downstream of the second turbine rotor for driving a propeller. A mount ring is secured between the second turbine rotor and the propeller. | 12-10-2015 |
20150361921 | Modifying Direct Drive Gas Turbine Engine Core to Provide a Geared Turbofan - A method comprises the steps of modifying a direct drive engine, which includes a first fan rotor, a high pressure compressor driven by a high pressure turbine on a first high spool and a first low pressure turbine designed to drive a first low pressure compressor on a first low spool, and the fan rotor all at the same speed. The modifying step includes providing a second fan rotor, second low spool, including a second low pressure compressor rotor and second low pressure turbine rotor and incorporating a gear reduction between a shaft driven by the second low pressure turbine rotor and the second fan rotor to provide a geared turbofan, such that at least a portion of the design of the high pressure compressor rotor, the combustor and the high pressure turbine rotor from the designed direct drive engine are utilized in the geared turbofan. A gas turbine engine is also disclosed. | 12-17-2015 |
20160047308 | MECHANICAL DRIVE ARCHITECTURES WITH LOW-LOSS LUBRICANT BEARINGS AND LOW-DENSITY MATERIALS - Mechanical drive architectures can include a gas turbine having a compressor section, a turbine section, and a combustor section. A load compressor is driven by the gas turbine. A rotor shaft extends through the gas turbine and the load compressor. At least one of the rotating components in one of the gas turbine and the load compressor includes a low-density material. Bearings support the rotor shaft within the gas turbine and the load compressor, at least one of the bearings being a low-loss lubricant bearing. | 02-18-2016 |
20160047335 | MECHANICAL DRIVE ARCHITECTURES WITH MONO-TYPE LOW-LOSS BEARINGS AND LOW-DENSITY MATERIALS - Mechanical drive architectures can include a gas turbine having a compressor section, a turbine section, and a combustor section. A load compressor is driven by the gas turbine. A rotor shaft extends through the gas turbine and the load compressor. At least one of the rotating components in one of the gas turbine and the load compressor includes a low-density material. Bearings support the rotor shaft within the gas turbine and the load compressor, at least one of the bearings being a mono-type low-loss bearing. | 02-18-2016 |
20180023480 | MULTI-SPOOL GAS TURBINE ENGINE ARCHITECTURE | 01-25-2018 |
060390162 | Counter - rotatable | 6 |
20090145102 | Gas Turbine Engine Systems Involving Tip Fans - Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the first rotatable set of blades defining an inner fan and a tip fan; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades. | 06-11-2009 |
20100287909 | HYDRAULIC STEPPER MOTOR - A hydraulic stepper motor comprising
| 11-18-2010 |
20120000177 | TURBINE ENGINE WITH NONSTREAMLINED IMPELLERS - The present invention relates to a turbine engine comprising two respectively upstream and downstream external impellers ( | 01-05-2012 |
20120023898 | GAS TURBINE ENGINE - A gas turbine engine includes, in flow series, a generator section and a free power turbine. The generator section includes one or more generator turbine stages. One or more respective generator drive shafts extend axially forwardly from the generator turbine stages to one or more corresponding compressor stages. The free power turbine includes a first turbine stage and a contra-rotating second turbine stage. The gas turbine engine further includes a first drive shaft extending axially from the free power turbine to transmit rotational drive from the first turbine stage to a first propeller. The gas turbine engine further includes a second drive shaft extending from the free power turbine coaxially with the first drive shaft to transmit contra-rotational drive from the second turbine stage to a contra-rotating second propeller. | 02-02-2012 |
20140290209 | GAS TURBINE APPARATUS - A gas turbine apparatus may include one or more driving shafts; a compressor configured to receive power from the one or more driving shafts, suck air, and compress the sucked air at high pressure. The gas turbine may include a combustor configured to mix the compressed air with fuel, and combust the fuel mixture to generate combustion gas. A turbine is connected to the one or more driving shafts and is configured to rotate while the combustion gas passes through the turbine. The turbine may include one or more first turbine blades configured to rotate in a first direction and one or more second turbine blades configured to rotate in a second direction opposite to the first direction. The one or more first turbine blades and the one or more second turbine blades may be alternately arranged along an axial direction of the turbine. | 10-02-2014 |
20150369174 | ROTARY UNITS, ROTARY MECHANISMS, AND RELATED APPLICATIONS - The invention relates to rotary units and rotary mechanisms that are suitable for use in numerous applications. Rotary units typically include rotational components that are configured to rotate. In some embodiments, for example, multiple rotary units are assembled in rotary mechanisms such that neighboring pairs of rotational components counter-rotate or contra-rotate relative to one another during operation of the rotary mechanisms. Rotational components generally include one or more implements that are structured to perform or effect one or more types of work as the rotational components rotate relative to one another in a given rotary mechanism. In certain embodiments, implements are configured to rotate and/or to effect the movement of other components as rotational components rotate. In some embodiments, engines include rotary mechanisms and are used in, for example, ground vehicles, marine vehicles, aircraft, or devices. | 12-24-2015 |
060390163 | Selectively connectable | 3 |
20080302082 | Power transmission arrangement - A power transmission arrangement comprises a first power transmission member connectable to a first main shaft of an engine. The arrangement also includes a second power transmission member connectable to a second main shaft of the engine and to a third power transmission member. A coupling assembly is provided which has a selectable coupling condition to couple the first power transmission member to the second power transmission member to allow power to be transmitted from the third power transmission member to the first main shaft of the engine via the first power transmission member. The coupling assembly has a decoupling condition to decouple the first power transmission member from the second power transmission member to allow power to be transmitted from the main shaft of the engine to the third power transmission member via the second power transmission member. | 12-11-2008 |
20130008144 | EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES - A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades. | 01-10-2013 |
20220136434 | TURBINE POSITIONING IN A GAS TURBINE ENGINE - A gas turbine engine for an aircraft includes an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core. The engine core further includes three bearings arranged to support the core shaft including a forward bearing and two rearward bearings, with a minor span defined as the distance between the two rearward bearings. A minor span to turbine length ratio is equal to or less than 1.05. | 05-05-2022 |
060390170 | With treatment between stages | 13 |
20090064654 | Turbine engine with modulated combustion and reheat chambers - A turbine engine includes a compressor, a combustor fluidly connected to the compressor and a first turbine operated by a combustion product formed in the first combustor. The turbine engine also includes a reheat chamber in which air, fuel, and exhaust gases from the first turbine are ignited to form a combustion product used to drive a second turbine. The engine further includes a controller that regulates at least one of an amount of fuel and compressed air delivered to the combustor and an amount of fuel, compressed air and exhaust gases delivered to the reheat chamber based on at least one turbine engine parameter measured by a sensor. | 03-12-2009 |
20090241505 | RE-HEAT COMBUSTOR FOR A GAS TURBINE ENGINE - A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second turbine portions. The re-heat combustor includes a combustion duct having a curvilinear flow portion. The curvilinear flow portion provides an increased residence time of combustion products passing through the re-heat combustor. | 10-01-2009 |
20100024381 | SYSTEM AND METHOD OF OPERATING A POWER GENERATION SYSTEM WITH AN ALTERNATIVE WORKING FLUID - A method of operating a turbine engine system and a turbine engine system are provided. The method comprises supplying a flow of oxygen to a combustion chamber defined within a plurality of turbines coupled serially together within the turbine engine system, supplying a flow of hydrocarbonaccous fuel to the combustion chambers of each of the plurality of turbines in the turbine engine system, and supplying a working fluid to an inlet of a first turbine engine coupled within the turbine engine system, wherein the working fluid is substantially nitrogen-free and wherein each of the turbines coupled within the turbine engine system is operable with the resulting fuel-oxygen-working fluid mixture. | 02-04-2010 |
20110214406 | Microturbine sun tracker - The invention relates electrical power generation using renewable sun energy in a Microturbine Sun Tracker (MST), a system for useful electrical output power that combines a Concentrated Solar Energy (CSE) with a closed cycle Microturbine powerplant. | 09-08-2011 |
20120036824 | REHEAT BURNER - A reheat burner ( | 02-16-2012 |
20120216502 | GAS TURBINE INTERCOOLER WITH TRI-LATERAL FLASH CYCLE - A gas turbine intercooler operates to heat a predetermined organic fluid via heat generated by the gas turbine. The heated organic fluid remains in a partially evaporated or non-evaporated liquid phase to provide a heated organic fluid that reaches a state of saturation with a vapor quality less than unity. An expansion machine expands the heated organic fluid via a Tri-Lateral Flash cycle to increase the vapor quality and generate electrical power therefrom. | 08-30-2012 |
20120285137 | GAS TURBINE ENGINE AND REHEAT SYSTEM - One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique reheat system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and reheat systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 11-15-2012 |
20130081373 | POWER PLANT - A power plant is provided and includes components for generating power from fluids at high and intermediate pressures, a pathway defined between the components along which a heated fluid flows to the one of the components for generating power from fluids at intermediate pressures and a circuit fluidly coupled to the pathway to cool a portion of the heated fluid prior to the portion of the heated fluid reaching the one of the components for generating power from fluids at intermediate pressures. | 04-04-2013 |
20130318941 | Supercharged Combined Cycle System With Air Flow Bypass - A system and method for supercharging a combined cycle system includes a forced draft fan providing a variable air flow. At least a first portion of the air flow is directed to a compressor and a second portion of the airflow is diverted to a heat recovery steam generator. A control system controls the airflows provided to the compressor and the heat recovery steam generator. The system allows a combined cycle system to be operated at a desired operating state by controlling the flow of air from the forced draft fan to the compressor and the heat recovery steam generator. | 12-05-2013 |
20140137534 | INTERNALLY COOLED SPOKE - A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case. | 05-22-2014 |
20150007547 | COMBUSTION DEVICE - The combustion device includes a burner, a combustion chamber downstream of the burner, a lance projecting into the burner for fuel and air injection, and a plenum that at least partly houses the burner. The plenum is connected to the inside of the lance to supply an oxidiser to it. | 01-08-2015 |
20160115826 | COMBINED CYCLE POWER PLANT - The present invention generally relates to a combined cycle power plant. More in particular, the present invention relates to a plant where the temperature of the flow of gas exiting the turbine is lowered without the need of employing high cost nickel alloys within the heat recovery steam generator. | 04-28-2016 |
20160376960 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow control system for a combined cycle turbomachine system in accordance with an embodiment includes: an airflow generation system for attachment to a rotatable shaft of a gas turbine system, the airflow generation system drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for extracting a first portion of the excess flow of air to provide bypass air, and for diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an airflow regulation system for diverting a second portion of the excess flow of air into the compressor component and, in response to an under-frequency grid event, for increasing the second portion of the excess flow of air diverted into the compressor component. | 12-29-2016 |