| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060722000 |
Combustion products generator
| 2136 |
| 060772000 |
Process
| 1964 |
| 060796000 |
Having mounting or supporting structure
| 340 |
| 060390150 |
Multiple fluid-operated motors
| 232 |
| 060390091 |
With safety device
| 162 |
| 060784000 |
For nominal other than power plant output feature
| 161 |
| 060390500 |
With exhaust treatment
| 119 |
| 060793000 |
Combined with regulation of power output feature
| 102 |
| 060801000 |
Convertible or combined with feature other than combustion products generator or motor
| 77 |
| 060390120 |
With combustible gas generator
| 73 |
| 060390461 |
Using special fuel or oxidizer
| 72 |
| 060390080 |
With lubricators
| 64 |
| 060786000 |
Combined with starting feature
| 51 |
| 060390830 |
Cooling of auxiliary components
| 31 |
| 060390370 |
Plural combustion products generators in ring coaxial with turbine
| 28 |
| 060799000 |
Having expansible connection
| 25 |
| 060390230 |
With variable oxidizer control
| 25 |
| 060390530 |
With addition of steam and/or water
| 24 |
| 060390340 |
Rotating combustion products generator and turbine
| 10 |
| 060390600 |
External-combustion engine type
| 9 |
| 060390480 |
With fluid pressure feeding of oxidizer, fuel or water
| 7 |
| 060390450 |
With gear, pressure exchanger, or screw-type compressor
| 7 |
| 060390190 |
Different fluids | 4 |
| 20120186219 | Hybrid Supercritical Power Cycle with Decoupled High-side and Low-side Pressures - The present invention generally relates to power generation methods and secondary processes yielding a supply of carbon dioxide. In one embodiment, the present invention relates to a supercritical carbon dioxide cycle power generator utilizing at least a portion of waste heat from the secondary process that also provides at least a portion of carbon dioxide within the supercritical carbon dioxide cycle. | 07-26-2012 |
| 20140007553 | HOT WATER INJECTION FOR TURBOMACHINE - A turbomachine is provided and includes a combustor in which a first compressed air is combustible along with fuel and which is receptive of water. The water is provided to the combustor subsequent to the water being used to cool a second compressed air, and the water is used to cool the second compressed air prior to the second compressed air being used to atomize the fuel. | 01-09-2014 |
| 20140182264 | AIRCRAFT ENGINE SYSTEMS AND METHODS FOR OPERATING SAME - A gas turbine propulsion system includes a system which utilizes a cryogenic liquid fuel for a non-combustion function. | 07-03-2014 |
| 20140283498 | GAS TURBINE SYSTEM - The gas turbine system (GT) includes a combustor ( | 09-25-2014 |
| 060804000 |
Coaxial combustion products generator and turbine | 2 |
| 20110209482 | TANGENTIAL COMBUSTOR WITH VANELESS TURBINE FOR USE ON GAS TURBINE ENGINES - A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annular combustor has an inner/outer shell having corrugated surfaces that extend radially outward and inward across an entire hot gas stream inside the annular combustor. The corrugations twist about the engine centerline in a longitudinal direction of travel of the engine. The resulting flow path accelerates and turns the hot gas stream to conditions suitable for introduction into the first stage turbine blades, which eliminate the need for first stage turbine vanes. The annular combustor is configured with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air. | 09-01-2011 |
| 20150121897 | GAS TURBINE ENGINE WITH SOFT MOUNTED PRE-SWIRL NOZZLE - An exemplary gas turbine engine may include a compressor, a turbine, and a combustor disposed between the compressor and the turbine. The combustor generally may have an inner casing. The exemplary gas turbine may further include a pre-swirl nozzle configured to receive a cooling stream. The cooling stream may be supplied from a cooled cooling air stream. The pre-swirl nozzle may further be configured to direct at least a portion of the cooling stream to the turbine. The pre-swirl nozzle may be flexibly mounted to the inner casing of the combustor. | 05-07-2015 |
| 060390490 |
With air injection by fuel or steam jet | 2 |
| 20080264033 | METHODS AND SYSTEMS TO FACILITATE REDUCING NOx EMISSIONS IN COMBUSTION SYSTEMS - A method for assembling a gas turbine combustor system is provided. The method includes providing a combustion liner including a center axis, an outer wall, a first end, and a second end. The outer wall is orientated substantially parallel to the center axis. The method also includes coupling a transition piece to the liner second end. The transition piece includes an outer wall. The method further includes coupling a plurality of lean-direct injectors along at least one of the liner outer wall and the transition piece outer wall such that the injectors are spaced axially apart along the wall. | 10-30-2008 |
| 20160102612 | Prime Mover with Recovered Energy Driven Compression of the Working Fluid - The present invention is a prime mover with recovered energy driven compression for stationary and motor vehicle application. Efficient low compression operation, especially beneficial to small gas turbines, is enabled with either ambient or cryogenic intake air. Recovered energy, liquefied air cooling and re-liquefaction of air by a cryogenic sink minimize motive fluid compression work of a jet compressor driving exhaust gas recirculation. Regenerative heat exchanger terminal temperature difference relative to turbine temperature drop and heat exchanger surface area are reduced. | 04-14-2016 |
| 060390430 |
With dual function turbine | 2 |
| 20090007539 | Screw Shaft Turbine Compressor - A screw shaft turbine compressor comprising (i) a compressor section, (ii) a turbine section, (iii) a combustion section coupling to the compressor section and the turbine section, and (iv) a grooved shaft. The grooved shaft in one embodiment extends from a portion of the compressor section, through the combustion section, and to a portion of the turbine section. | 01-08-2009 |
| 20090113871 | ROTORCRAFT FITTED WITH TURBINE ENGINES - The invention relates to a rotorcraft ( | 05-07-2009 |
| 060390420 |
With reversible turbine | 1 |
| 20160169102 | REVERSE CORE FLOW GAS TURBINE ENGINE | 06-16-2016 |
| 060390130 |
Automatic starting and stopping of combustion products generator | 1 |
| 20130213002 | GAS TURBINE START/STOP APPARATUS - A start/stop apparatus includes: a transfer rotation shaft which rotates with a gas turbine; a hydraulic pump which continuously generates a predetermined oil pressure; a high-pressure oil accumulation portion which is introduced the oil pressure which generated by the hydraulic pump; a low-pressure oil accumulation portion which is introduced the oil pressure which generated by the hydraulic pump, and the pressure of the low-pressure oil accumulation portion is set to be lower than that of the high-pressure oil accumulation portion; a hydraulic motor which rotates the transfer rotation shaft using the oil pressure; a hydraulic switch valve which introduces either oil pressure of the high-pressure oil accumulation portion or the low-pressure oil accumulation portion in the hydraulic motor; and a rotation controller which controls the hydraulic motor based on the rotation speed of the gas turbine. | 08-22-2013 |
| Entries |
| Document | Title | Date |
|---|
| 20090313965 | RADIAL BALL BEARING - A bearing assembly includes an outer race and an inner race with a ball bearing element located between the inner and the outer races. The inner race has a first portion and a second portion separated from the first portion by a split. The first portion includes a first curved inner race support surface defined by a first center point and the second portion includes a second curved inner race support surface defined by a second center point that is non-coincident with the first center point. | 12-24-2009 |
| 20100326039 | GAS TURBINE, DISK, AND METHOD FOR FORMING RADIAL PASSAGE OF DISK - A gas turbine includes a disk rotatable about a rotational axis, when turbine rotor blades for receiving combustion gas obtained by burning fuel are connected to the side periphery, and energy of the combustion gas received by the turbine rotor blades is transmitted, and a radial passage that, in a cross-section at a virtual curved plane that is a curved plane about the rotational axis and in which distances from all points on the curved plane to the rotational axis are all equal, is a hole formed to include a portion having a shape in which the length in the circumferential direction of the disk is longer than the length in the direction parallel to the rotational axis, and is formed in the disk from the side of the rotational axis toward the outside of the disk. | 12-30-2010 |
| 20110138765 | MAGNETIC ADVANCED GENERATION JET ELECTRIC TURBINE - Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exo-skeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation over traditional gas turbine technology today. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture. Engine performance may be controlled across the entire desired flight envelope, whether subsonic, transonic or supersonic flight conditions. With bypass fan(s), compressor stages and turbine segments controlled electrically in a shaftless turbine design, the S-MAGJET maximizes the propulsion efficiencies over a broader range of operating conditions compared to current art of turbine technology and at much higher thermodynamic and aerodynamic efficiencies. | 06-16-2011 |
| 20110302901 | ZONAL MAPPING FOR COMBUSTION OPTIMIZATION - A method of optimizing operation of a furnace to control emission within a system. Each furnace zone inside of the furnace is associated with at least one exhaust zone. A signal indicative of an amount of byproduct exiting the furnace through at least one of the exhaust zones is received from one or more of the sensors. Based on this signal, an offending furnace zone is identified from among the plurality of furnace zones, the offending furnace zone including an oxygen level contributing to the amount of the byproduct. A relative adjustment of at least one of an amount of oxygen being introduced into the offending furnace zone, and an angular orientation of an oxygen injector introducing oxygen into the offending furnace zone relative to a focal region within the furnace can be initiated. The furnace may have structure to perform the method and may be part of a system. | 12-15-2011 |
| 20110314788 | Aircraft Turbine Engine And Use Of Such A Turbine Engine - The invention relates to an aircraft turbine engine and to the use of such a turbine engine. According to the invention, the turbine engine (la) comprises a means for shifting the axis (la-la) of the blower ( | 12-29-2011 |
| 20120031067 | TURBULATED ARRANGEMENT OF THERMOELECTRIC ELEMENTS FOR UTILIZING WASTE HEAT GENERATED FROM TURBINE ENGINE - Disclosed is a turbulated arrangement of thermoelectric elements for utilizing waste heat generated from a turbine engine. The turbulated arrangement of thermoelectric elements is located within the turbine casing at a heat exhaust end of the turbine engine. The turbulated arrangement of thermoelectric elements convert heat exhaust generated from the turbine engine into electrical energy. In one embodiment, the electrical energy generated from the turbulated arrangement of thermoelectric elements can be used to power electrical components located about the turbine engine. | 02-09-2012 |
| 20120317955 | SURGE MARGIN CONTROL - A gas turbine engine control system comprising a variable stator vane schedule for normal operation of the gas turbine engine. The system is configured to generate an arm signal indicating potential shaft break. Then the system is configured to alter the variable stator vane schedule to slew each variable stator vane to decrease the available surge margin in response to the arm signal. Or the system is configured to limit a response rate of a variable stator vane actuator in response to the arm signal. Or the system is configured to alter the variable stator vane schedule and limit the response rate of the actuator. | 12-20-2012 |
| 20120324859 | HEAT EXCHANGER - A heat exchanger is provided for warming fuel prior to introduction of the fuel to an engine, the heat exchanger including: a fuel inlet and a fuel outlet; a heat exchange matrix having heat transfer components past which the fuel flows between said inlet and said outlet and which are arranged to be heated; and swirl inducing means arranged between said inlet and said matrix arranged to cause fuel from said inlet to swirl prior to entering said matrix. By causing the fuel to swirl prior to entering the heat exchange matrix, entrained ice in the fuel can be caused to concentrate at an outer region of the heat exchanger thereby allowing fuel to continue to flow through the heat exchanger to the engine even when ice is present in the fuel. | 12-27-2012 |
| 20130212999 | CONTROL SYSTEM - A control system for at least one of steam turbines, gas turbines or power plants includes a sensor system configured to monitor predefined operating parameters, the sensor system including redundant sensors. A central processor arrangement of the control system has an input side configured to receive measurement data from the sensor system and an output side configured to communicate with operation control elements of the turbines or power plants. A sensor side processor circuit is assigned at least to the redundant sensors, the processor circuit being configured to continuously check the sensors for error-free operation, to protect or block the input side of the central processor arrangement from erroneous signals, and to only respectively forward or further process signals from a sensor that has been identified as error-free in one channel. | 08-22-2013 |
| 20130283756 | MANIFOLD FOR GAS TURBINE ENGINE - A manifold assembly for a gas turbine engine includes a mounting plate configured for attachment to a housing structure and a flow plate that is attached to the mounting plate. One or more flow passages are defined between the mounting plate and flow plate. | 10-31-2013 |
| 20130298522 | GEARED FAN ASSEMBLY - An assembly for a gas turbine engine, with a gearbox including a first portion having a first input gear coupled to a rotatable turbine shaft, a first output gear, and defining a first transmission path between the first input and output gears, and a second portion having a second input gear coupled to the turbine shaft, a second output gear, and defining a second transmission path between the second input and output gears different from the first transmission path. A fan rotor is coupled to the first output gear and a booster rotor is coupled to the second output gear on a same side of the gearbox than the coupling between the fan rotor and the first output gear. A method of assembling a drive for a fan rotor and a booster rotor in a gas turbine engine is also disclosed. | 11-14-2013 |
| 20130327010 | WAVE DISC ENGINE APPARATUS - A wave disc engine apparatus is provided. A further aspect employs a constricted nozzle in a wave rotor channel. A further aspect provides a sharp bend between an inlet and an outlet in a fluid pathway of a wave rotor, with the bend being spaced away from a peripheral edge of the wave rotor. A radial wave rotor for generating electricity in an automotive vehicle is disclosed in yet another aspect. | 12-12-2013 |
| 20140090352 | SEALING SYSTEM FOR A CONTINUOUS FEED SYSTEM OF A GASIFIER - A modular power generation system including a gasification reactor 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 include a reactor vessel with distinct reaction zones that facilitate greater control and a more efficient system. The system may include a sealing system for a continuous feed system of a gasifier enabling an inlet opening of a feedstock system to remain open yet seal the reactor without a mechanical 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 with in the fuel. | 04-03-2014 |
| 20140182263 | Maphbe Turbine - The Maphbe Turbine is a system of nozzles, rotors, and energy storage devices used to generate consistent power from intermittent energy sources specifically wind. It uses sails, cables, and poles as a way to form large nozzles and rotors for power generation, these systems can be paired with other renewable sources for co-generation, and can be used for powering pumped storage hydro stations, excess energy can be stored in multi-layer carbon nanotube capacitors. Another application for the invention is offshore floating wind farms to make giant collapsible nozzles and turbines paired with solar, and or wave energy devices. | 07-03-2014 |
| 20140202130 | MULTI-COLOR PYROMETRY IMAGING SYSTEM AND METHOD OF OPERATING THE SAME - A multi-color pyrometry imaging system for a high-temperature asset includes at least one viewing port in optical communication with at least one high-temperature component of the high-temperature asset. The system also includes at least one camera device in optical communication with the at least one viewing port. The at least one camera device includes a camera enclosure and at least one camera aperture defined in the camera enclosure, The at least one camera aperture is in optical communication with the at least one viewing port. The at least one camera device also includes a multi-color filtering mechanism coupled to the enclosure. The multi-color filtering mechanism is configured to sequentially transmit photons within a first predetermined wavelength band and transmit photons within a second predetermined wavelength band that is different than the first predetermined wavelength band. | 07-24-2014 |
| 20140215997 | Flexible Shield for Fluid Connectors - A flexible shield for fluid connectors of a gas turbine engine is disclosed. The flexible shield may comprise a flexible sleeve adapted to surround the fluid connector, and a coupling configured to secure the flexible sleeve onto a fluid tube proximate the fluid connector. A gas turbine engine employing such a flexible shield is also disclosed, as is a method of enclosing a fluid connector in a gas turbine engine using such a flexible shield. | 08-07-2014 |
| 20140373503 | METHOD OF FINISHING A BLADE - An automated technique for finishing gas turbine engine blades or vanes by generating a bespoke tooling path for each blade or vane. The bespoke tooling path is generated by scanning the aerofoil surface to generate a 3-D electronic representation of the surface. The 3-D electronic surface is then analysed to identify imperfections or defects, and then a machining path a generated through which the imperfections can be removed. The machining path is determined so as to smoothly blend the surface back to the underlying surface where the imperfections had been present. In this way, the resulting aerofoil, once machined, has optimized aerodynamic performance. | 12-25-2014 |
| 20150068188 | TURBINE ENGINE, ENGINE STRUCTURE, AND METHOD OF FORMING AN ENGINE STRUCTURE WITH THERMAL BARRIER COATING PROTECTION - A turbine engine, an engine structure, and a method of forming an engine structure are provided herein. In an embodiment, an engine structure includes a metal substrate, a thermal barrier coating layer, and a metal silicate protective layer. The thermal barrier coating layer overlies the metal substrate, and the thermal barrier coating layer has columnar grains with gaps defined between the columnar grains. The metal silicate protective layer is formed over the thermal barrier coating layer, and the metal silicate protective layer covers the columnar grains and the gaps between the columnar grains. | 03-12-2015 |
| 20150308337 | GAS TURBINE ENGINE COMPONENT WITH EMBEDDED DATA - A component for a gas turbine engine is disclosed. The component includes at least a first portion and a second portion, and a data representing matrix. The second portion includes a second portion surface. The data representing matrix is formed directly on the second portion surface and includes a plurality of contrasting cells arranged in a geometric pattern representing information about the component including test data, a serial number, and a part number. The plurality of contrasting cells includes a plurality of first cells and a plurality of second cells that contrast from the plurality of first cells. | 10-29-2015 |
