Class / Patent application number | Description | Number of patent applications / Date published |
060726000 | With means to pressurize oxidizer for combustion or other purposes | 72 |
20090193809 | METHOD AND SYSTEM TO FACILITATE COMBINED CYCLE WORKING FLUID MODIFICATION AND COMBUSTION THEREOF - A method of assembling a combustion system includes providing a gas turbine engine that includes a gas turbine section coupled downstream from a combustion chamber and coupling a source of oxygen to the gas turbine engine such that a stream of oxygen discharged from the source facilitates displacing nitrogen in the working fluid of the gas turbine engine and facilitates decreasing emissions generated within the gas turbine engine. | 08-06-2009 |
20110126542 | METHOD AND DEVICE FOR THE TREATMENT OF PRODUCT GAS PRODUCED BY PRESSURE GASIFICATION OF SOLID FUELS - Upon cooling to 15 to 45° C., a process for the treatment of raw product gas generated by pressure gasification of solid fuels comprises the removal of HCN and NH3 in a preliminary stage, of H2S and COS and possibly other sulfur-containing compounds in a first stage and of CO2 in a second stage by physisorption with cold oxygenate, and the pure product gas is supplied to the direct reduction of iron ore as reduction gas and/or as fuel gas. An improvement of the process consists in that recycle gas loaded with CO2 and steam, which is branched off from the circuit of the recycle gas of the direct reduction of iron ore, is admixed to the desulfurized product gas upon removal of the steam contained therein. | 06-02-2011 |
20130074502 | TRANSITION PIECE OF COMBUSTOR, GAS TURBINE HAVING THE SAME, AND PRODUCING METHOD FOR TRANSITION PIECE - A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove. | 03-28-2013 |
20130086907 | JET FLOW NOZZLE AND JET ENGINE - The present invention relates to a jet engine including protrusions ( | 04-11-2013 |
20130086908 | GAS TURBINE COMBUSTION CHAMBER ARRANGEMENT OF AXIAL TYPE OF CONSTRUCTION - A gas-turbine combustion chamber arrangement includes a flame tube, a diffuser element arranged upstream of the flame tube in the flow direction, the diffuser element including an annular duct, and an axial compressor arranged upstream of the diffuser element. The diffuser element features an annular guide vane area in which guide vanes are arranged, which for redirecting an incoming flow are provided at an angle (α) in a range between 28° and 32° relative to a central axis of the gas turbine. Downstream of the guide vane area, a diffuser area is arranged, the diffuser area not being provided with flow-guiding elements affecting the flow, where burners arranged in the annular combustion chamber are provided with their burner axes at an angle (β) between 40° and 50° relative to the central axis. | 04-11-2013 |
20130111907 | HOLLOW FAN BLADE TUNING USING DISTINCT FILLER MATERIALS - A fan blade comprises a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. Material is deposited within the channels, with one type of material being selected to provide additional stiffness to the fan blade, and a second type of material being selected for having good damping characteristics. A method and gas turbine engine are is also disclosed. | 05-09-2013 |
20130111908 | FAN ROTOR BLADE AND FAN - A fan rotor blade includes a blade body constructed of a composite material, a blade root constructed of the composite material, and a sheath attached to a leading edge of the blade body. The sheath includes a sheath main body and a pair of joint flanges, and is segmented into a sheath base segment and a sheath top segment. The sheath top segment has a longer length than a length of the sheath base segment along a span direction. A sheath length of the sheath main body at an assumed impact position with an obstacle is not shorter than 10% chord and not longer than 60% chord. A sheath length of the sheath along an end edge of the fan rotor blade is not shorter than 40% chord. The fan rotor blade possesses sufficient impact resistance and can be simplified and light-weighted. | 05-09-2013 |
20130160454 | GAS TURBINE ENGINE WITH SUPERSONIC COMPRESSOR - A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct. | 06-27-2013 |
20130312419 | GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION - A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supporting the shaft relative to the inlet case. The second bearing is arranged radially outward from the shaft. | 11-28-2013 |
20130318972 | GAS TURBINE APPARATUS WITH IMPROVED EXERGY RECOVERY - A gas turbine apparatus comprising a compressor adapted to compress air; a combustion chamber, disposed downstream of the compressor and adapted to receive and combust a first portion of the compressed air is disclosed. The gas turbine apparatus further comprises a turbine, disposed downstream of the combustion chamber and adapted to receive and perform work from the combusted and compressed air, and a heat exchanger comprising a cooler, disposed parallel to the combustion chamber, downstream of the compressor and upstream of the gas turbine, which is adapted to receive and cool at least a second portion of the compressed air and provide the cooled compressed air to at least one thermally loaded part of the gas turbine. In addition, the gas turbine apparatus comprises at least one super-heater assembly, disposed downstream of the compressor and upstream of the cooler, adapted to extract and transfer energy from the compressed air to the combustion chamber and/or the turbine and/or an auxiliary energy recovering system, utilizing at least one auxiliary working medium adapted to transfer the energy. | 12-05-2013 |
20130318973 | Axial Compressor and Gas Turbine Having Axial Compressor - An axial compressor that can remove an attachment within a groove of a casing and recover an effect of suppressing stall on rotor blades, and a gas turbine provided with the axial compressor, are provided. The axial compressor includes a compressor body | 12-05-2013 |
20130318974 | GAS TURBINE - Disclosed is a gas turbine which includes: a gas expansion part that expands gas; a power generation part that generates a rotational force due to the gas expanded by the gas expansion part and has a turbine shaft so as to transfer the rotational force; and an air compression part that is combined with the turbine shaft of the power generation and rotates and compresses air so as to supply compressed air to the gas expansion part. The power generation part generates the rotational force when a nozzle assembly having at least one injection hole so as to inject the gas in a circumferential direction is combined with the turbine shaft and the gas is injected in the circumferential direction via the at least one injection hole. | 12-05-2013 |
20140000262 | GAS TURBINE ENGINE COMPONENT WITH DISCHARGE SLOT HAVING OVAL GEOMETRY | 01-02-2014 |
20140020390 | CLEARANCE CONTROL FOR GAS TURBINE ENGINE SEAL - A gas turbine engine section has a rotor carrying a plurality of blades. The blades have airfoils which define a radially outer tip. A blade outer air seal is positioned radially outwardly of the tips of the blades. The blade outer air seal is provided by at least a plurality of circumferentially spaced segments, which slide circumferentially relative to each other to adjust an inner diameter of an inner surface of the blade outer air seal segments. An actuator actuates the blade outer air seal segments to slide towards each other to control a clearance between the inner periphery of the blade outer air seal segments and the radially outer tip of the blade airfoils. A gas turbine engine is also disclosed. | 01-23-2014 |
20140033720 | Controller for Gas Turbine Power Plant - A controller for use in a gas turbine power plant includes a compressor that compresses combustion air; a water-atomization cooling apparatus that sprays water drops of atomized water supplied via a water-atomization flow-rate regulating valve over a flow of air drawn in the compressor; a combustor that mixes the compressed combustion air with fuel to thereby burn a fuel-air mixture and generate combustion gas at high temperature and performs combustion switching during operation; a turbine that uses the combustion gas to drive the compressor and a generator; the water-atomization flow-rate regulating valve that controls a flow rate of the atomized water; and a compressor inlet inner blade that controls a flow rate of air drawn in the compressor. The controller includes control means that calculates a fuel-air ratio correction command signal for compensating for reduction in a fuel-air ratio in the combustor occurring during the combustion switching. | 02-06-2014 |
20140047842 | SUCTION SIDE TURBINE BLADE TIP COOLING - An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket. | 02-20-2014 |
20140047843 | PLATFORM COOLING CIRCUIT FOR A GAS TURBINE ENGINE COMPONENT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity. | 02-20-2014 |
20140053560 | HIGH EFFICIENCY POWER GENERATION SYSTEM AND SYSTEM UPGRADES - A thermal/electrical power converter includes a gas turbine with an input couplable to an output of an inert gas thermal power source, a compressor including an output couplable to an input of the inert gas thermal power source, and a generator coupled to the gas turbine. The thermal/electrical power converter also includes a heat exchanger with an input coupled to an output of the gas turbine and an output coupled to an input of the compressor. The heat exchanger includes a series-coupled super-heater heat exchanger, a boiler heat exchanger and a water preheater heat exchanger. The thermal/electrical power converter also includes a reservoir tank and reservoir tank control valves configured to regulate a power output of the thermal/electrical power converter. | 02-27-2014 |
20140069100 | COMPACT DOUBLE GROUNDED MECHANICAL CARBON SEAL - A disclosed intershaft seal assembly for a gas turbine engine includes a support fixed to a static structure. A first seal housing is supported radially outboard of the support for holding a first seal. A second seal housing is supported radially inboard of the support and supports a second seal. A first biasing member is provided between the support and the first seal housing that biases the first seal housing in a first direction away from the support. A second biasing member between the support and the second seal housing biases the second seal housing in a second direction away from the support. | 03-13-2014 |
20140069101 | COMPRESSOR FAIRING SEGMENT - A compressor fairing segment includes a body having an upstream surface, a downstream surface, and opposing side surfaces between the upstream and downstream surfaces. A first detent on the upstream surface is shaped to conform to a first complementary fitting inside a compressor. A second detent on the downstream surface shaped to conform to a second complementary fitting inside the compressor. | 03-13-2014 |
20140075947 | 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 and a cooling circuit disposed inside of the body portion. The cooling circuit includes a first baffle received within a first core cavity that extends inside of the body portion, a second baffle received within a second core cavity that extends inside of the body portion, and a first rib disposed between the first core cavity and the second core cavity. The first baffle is in fluid communication with the second baffle through the first rib. | 03-20-2014 |
20140075948 | Fire Seal - A fire seal includes a molded body having a base portion, a curved portion extending from the base portion, and a metal seal support surrounding said base portion and a radially inward surface of said curved portion. The curved portion has a partially circular cross section. | 03-20-2014 |
20140083099 | MULTI-STAGE HIGH PRESSURE COMPRESSOR CASE - A compressor case assembly according to an exemplary embodiment of this disclosure, among other possible things, includes a case. A plurality of vane stages circumscribe an interior of the case. Each of the plurality of vane stages include a vane guide and at least one window for inserting a respective at least one vane there through. The at least one window is axially aligned with each of the vane guides The at least one window extends from an outer surface of the case into each of the vane guides. | 03-27-2014 |
20140090380 | Endwall Controuring - An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall near the leading edge of at least one of said plurality of airfoils, and a concave profiled region in the endwall near a middle of at least one of said plurality of flow passages. | 04-03-2014 |
20140182293 | Compressor Rotor for Gas Turbine Engine With Deep Blade Groove - A compressor rotor has a rotor centered on an axis, and a groove with opposed side edges. The groove receives a plurality of removable compressor blades, and has tangential sides. The tangential side surfaces are in contact with said tangential sides of the groove, and at least one slot is cut into the side edges. A first radial distance is measured from a radially outer edge of the side edge to a radially outer beginning point of the tangential sides of the groove. A second radial distance is radially between the radially outer beginning point of the tangential sides to a radially inner end of the tangential sides of the groove. A ratio of the first and second radial distance is between 1.1 and 5.0. | 07-03-2014 |
20140290252 | GAS TURBINE ENGINE PROVIDED WITH SCROLL - A gas turbine engine having high reliability is provided by suppressing occurrence of thermal stress between a scroll and a support member thereof. A gas turbine engine equipped with a combustor of a single-can type includes a scroll to guide a combustion gas fed from a combustor to a turbine while swirling the combustion gas about a rotation axis, a flange member to support the scroll with respect to the gas turbine engine from an inner peripheral side of the scroll, and a coupling member of an annular shape to couple the scroll and the flange member with each other. The scroll and the flange member are connected to the coupling member such that the scroll and the flange member are not in direct contact with each other. | 10-02-2014 |
20140311149 | GAS TURBINE ENGINE FAN BLADE AIRFOIL PROFILE - A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location. | 10-23-2014 |
20140318133 | THRUST EFFICIENT TURBOFAN ENGINE - A turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air, a power turbine converting the gas stream flow into shaft power, the power turbine rotating at a first relative rotational speed, a speed reduction device driven by the power turbine, and a propulsor section including a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path, wherein an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first relative rotational speed of the power turbine is less than about 0.15 at a take-off condition. | 10-30-2014 |
20140338333 | GAS TURBINE ENGINES HAVING PLASMA FLOW-CONTROLLED INTAKE SYSTEMS - Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure. | 11-20-2014 |
20140338334 | AIRCRAFT PROPULSION GAS TURBINE ENGINE WITH HEAT EXCHANGE - One embodiment of the present invention is a unique aircraft propulsion gas turbine engine. Another embodiment is a unique gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines with heat exchange systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 11-20-2014 |
20140338335 | HIGH EFFICIENCY POWER GENERATION SYSTEM AND SYSTEM UPGRADES - A thermal/electrical power converter includes a gas turbine with an input couplable to an output of an inert gas thermal power source, a compressor including an output couplable to an input of the inert gas thermal power source, and a generator coupled to the gas turbine. The thermal/electrical power converter also includes a heat exchanger with an input coupled to an output of the gas turbine and an output coupled to an input of the compressor. The heat exchanger includes a series-coupled super-heater heat exchanger, a boiler heat exchanger and a water preheater heat exchanger. The thermal/electrical power converter also includes a reservoir tank and reservoir tank control valves configured to regulate a power output of the thermal/electrical power converter. | 11-20-2014 |
20150047358 | INNER BARREL MEMBER WITH INTEGRATED DIFFUSER FOR A GAS TURBOMACHINE - An inner barrel member for a gas turbomachine includes a body having an outer surface, an inner surface and one or more radial flow splitters provided on the outer surface. The one or more radial flow splitters are configured and disposed to be arranged along a combustor centerline at a combustion flow outlet radially inwardly of a transition piece. | 02-19-2015 |
20150047359 | AXIAL FLOW MACHINE COOLING SYSTEM - This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine. | 02-19-2015 |
20150052897 | METHOD OF RECOVERING ENERGY IN A STEAM-COOLED GAS TURBINE - A method of recovering heat energy from a cooling medium used to cool hot gas path components in a turbine engine includes cooling one or more hot gas path components with the cooling medium; supplying spent cooling medium used to cool the one or more hot gas path components to a heat exchanger; supplying air (e.g., compressor discharge air) to the heat exchanger so as to be in heat exchange relationship with the spent cooling medium and thereby add heat to the compressor discharge air; and supplying the air heated in the heat exchanger to at least one combustor. | 02-26-2015 |
20150052898 | COMPONENTS HAVING VIBRATION DAMPERS ENCLOSED THEREIN AND METHODS OF FORMING SUCH COMPONENTS - A component formed by an additive manufacturing process includes a body and a first vibration damper. The body is formed from an additive manufacturing material, and defines at least a first cavity completely enclosed within the body. The first vibration damper is disposed within the first cavity. The first vibration damper includes a flowable medium and a first solidified element formed from the additive manufacturing material. The flowable medium surrounds the first solidified element. | 02-26-2015 |
20150068209 | METHOD FOR DETERMINING CIRCUMFERENTIAL SENSOR POSITIONING - A method for positioning sensors about a sensor ring includes the steps of assigning each sensor in a plurality of sensors a sensor number selected from a set of sensor numbers, where the set of sensor numbers is a whole number in the range of 0 to N, and where N is the total number of sensors in said plurality of sensors minus one, disposing a first sensor at a circumferential angular position zero on the sensor ring, and disposing each sensor in the plurality of sensors at a circumferential angular position about the sensor ring, wherein the circumferential angular position is defined by an offset from a circumferential angular position zero and the offset is equal to a base arc length between sensors multiplied by the sensor number of the sensor plus a base offset arc length multiplied by the sensor number of the sensor. | 03-12-2015 |
20150101333 | ROTATIONAL MACHINE - A rotational machine such as a turbocompressor has a fluid recovery system for recovering leaked working fluid such as gaseous helium in a helium circuit which has leaked past a shaft seal, a purifier being provided for removing contaminants from the working fluid, and turbocompressor may have one fluid such as helium or hydrogen working through one turbo component such as a turbine thereof and a second working fluid such as air or helium working through a second turbo component such as a compressor thereof, the rotational machine being installable in an engine of a flying machine. | 04-16-2015 |
20150121880 | INTERFACE ASSEMBLY FOR A COMBUSTOR - An interface assembly for a combustor includes an interface housing having a channel defined by a forward wall and at least one aft wall segment, the aft wall segment operatively coupled to an aft flange of a flow sleeve. Also included is a piston ring fittingly disposed in the channel. | 05-07-2015 |
20150128598 | COOLING AIR TEMPERATURE REDUCTION USING NOZZLES - A converging-diverging nozzle that has particular application for providing a cooling air flow to ring segments in a gas turbine engine. The engine includes a turbine section that receives a hot working gas. The turbine section includes at least one row of vanes, at least one row of blades and a plurality of ring segments forming at least one ring. The ring segments and the vanes are mounted to a vane carrier, where the vane carrier includes a cooling flow channel for each of the ring segments that receives an air flow to cool the ring segments. A plug is provided in each channel and has an internal bore shaped to define the converging-diverging nozzle through which the air flows so as to create a supersonic flow that reduces the temperature of the air and thus provides more cooling for the same amount of air flow. | 05-14-2015 |
20150135715 | Cooling System for Gas Turbine - The invention provides a gas turbine cooling system that efficiently cools a first-stage turbine wheel and the attachment portions of first-stage turbine blades. | 05-21-2015 |
20150300258 | COOLING HOLE ARRANGEMENT FOR ENGINE COMPONENT - A component for a gas turbine engine according to an exemplary aspect of this disclosure includes a surface having a plurality of cooling holes. The surface includes a first region and a second region each having a plurality of cooling holes. The cooling holes within the first region are arranged differently than the cooling holes in the second region. | 10-22-2015 |
20150308352 | GAS TURBINE ENGINE WITH FAN-TIED INDUCER SECTION - A gas turbine engine includes a shaft, a speed reduction device driven by the shaft, and a fan including a fan rotor driven by the speed reduction device. A compressor section has a plurality of compressor stages driven by the shaft. At least one inducer stage is positioned aft of the fan and coupled for rotation with the fan rotor. The at least one inducer stage is positioned upstream of the compressor section. | 10-29-2015 |
20150330302 | 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. | 11-19-2015 |
20150345384 | REVERSE CORE GEAR TURBOFAN - A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed. | 12-03-2015 |
20150354461 | ENGINE SYSTEMS AND METHODS FOR REMOVING PARTICLES FROM TURBINE AIR - A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section. | 12-10-2015 |
20150369488 | TURBINE AIR FLOW CONDITIONER - A turbine combustor section has a flow conditioner including a plurality of conduits arranged to convey pressurized air to an air chamber for entrance into a plurality of fuel nozzles. Each conduit includes an inlet configured to receive the pressurized air from an annular passage and an outlet configured to deliver the pressurized air to the air chamber. A cross-sectional area of each conduit varies between the inlet and the outlet so as to reduce a pressure drop across the flow conditioner. | 12-24-2015 |
20160003145 | GAS TURBINE ENGINE INLET - A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5. | 01-07-2016 |
20160032825 | GAS TURBINE ENGINE WITH SUPERSONIC COMPRESSOR - A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct. | 02-04-2016 |
20160061054 | STRUCTURAL FRAME INTEGRATED WITH VARIABLE-VECTORING FLOW CONTROL FOR USE IN TURBINE SYSTEMS - The present disclosure provides systems and apparatuses for use in turbine systems that integrate structural frame elements into a variable-vectoring flow control configuration in order to reduce the weight and length of such turbine systems. In one exemplary embodiment, an apparatus for directing a gas flow includes an annular outer structural casing, an annular central hub disposed within the outer structural casing, and a plurality of structural support elements extending radially between the central hub and the outer structural casing. The apparatus further includes a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the central hub and the outer structural casing and positioned circumferentially along the central hub between ones of the plurality of structural support elements. | 03-03-2016 |
20160131158 | COMPRESSOR AND GAS TURBINE - This compressor is provided with: a rotor casing that encircles a rotor, which rotates around a rotational axis; an air bleed chamber casing that is provided to the outer peripheral side of the rotor casing and demarcates an air bleed chamber interconnecting to a primary duct via a slot; and an air bleed tube that is connected to the air bleed chamber casing from the outer peripheral side and is provided with an air bleed pathway. In the slot, at which an opening to the primary duct is formed, a large opening, at which the opening area of the opening is locally larger than that of the other positions in the peripheral direction of the opening, is formed at a position in the peripheral direction corresponding to the position at which the air bleed tube is provided. | 05-12-2016 |
20160169159 | DEVICE FOR PRESSURIZING A PROPELLANT TANK OF A ROCKET ENGINE | 06-16-2016 |
20180023474 | BOUNDARY LAYER COOLING AIR FOR EMBEDDED ENGINE | 01-25-2018 |
060727000 | With oxidizer accumulator | 3 |
20110094229 | ADIABATIC COMPRESSED AIR ENERGY STORAGE SYSTEM WITH COMBUSTOR - A system includes a drive shaft, a motor-generator coupled to the drive shaft, a compressor coupled to the drive shaft and configured to output compressed air to a cavern, and a turbine coupled to the drive shaft and configured to receive air from the cavern. The system includes a first thermal energy storage (TES) device, a combustor configured to combust a flammable substance and generate an exhaust stream to the turbine, and controller. The controller is configured to control flow of the air to heat the air as it passes through the first TES, cause the flammable substance to flow to the combustor, operate the combustor to combust the air with the flammable substance to generate an exhaust stream into the turbine, and control the motor-generator to generate electrical energy from energy imparted thereto from the turbine via the drive shaft. | 04-28-2011 |
20110094230 | SYSTEM AND METHOD FOR CARBON DIOXIDE CAPTURE IN AN AIR COMPRESSION AND EXPANSION SYSTEM - A system includes a compression system fluidly coupled to a compartment to compress a first quantity of gas for storage in the compartment, the compression system including a compression path to convey the first quantity of gas; an expansion system fluidly coupled to the compartment to expand a second quantity of gas from the compartment, the expansion system including an expansion path to convey the second quantity of gas; a first path fluidly coupled to the compression path to convey the first quantity of gas to the compartment; a second path fluidly coupled to the expansion path to convey the second quantity of gas from the compartment to the expansion system; and a separation unit fluidly coupled to one of the first path, second path, compression path, and expansion path, wherein the separation unit removes a quantity of carbon dioxide from one of the first and second quantities of gas. | 04-28-2011 |
20110094231 | ADIABATIC COMPRESSED AIR ENERGY STORAGE SYSTEM WITH MULTI-STAGE THERMAL ENERGY STORAGE - An ACAES system operable in a compression mode and an expansion mode of operation is disclosed and includes a compressor system configured to compress air supplied thereto and a turbine system configured to expand compressed air supplied thereto, with the compressor system including a compressor conduit and the turbine system including a turbine conduit. The ACAES system also includes a plurality of thermal energy storage (TES) units positioned on the compressor and turbine conduits and configured to remove thermal energy from compressed air passing through the compressor conduit and return thermal energy to air passing through the turbine conduit. The compressor conduit and the turbine conduit are arranged such that at least a portion of the plurality of TES units operate at a first pressure state during the compression mode of operation and at a second pressure state different from the first pressure state during the expansion mode of operation. | 04-28-2011 |
060728000 | Having oxidizer cooling means | 17 |
20080276617 | Configurations and Methods For Thermal Integration of Lng Regasification and Power Plants - Contemplated plants integrate regeneration of a freeze point depressant with LNG regasification and a power cycle. Most preferably, the plant is a combined cycle plant in which heat for reboiling the regenerator is provided by the steam cycle, and in which LNG refrigeration content is used to condense steam from the regenerator and to further subcool intake air for a combustion turbine. | 11-13-2008 |
20090049836 | Thermally powered turbine inlet air chiller heater - An improvement to the air compressor of a combustion turbine system is disclosed, which makes the air compression more energy efficient plus have higher capacity on warm days. The same equipment with minimal modification is used to prevent inlet air icing conditions on cold days. Referring to FIG. | 02-26-2009 |
20100146976 | Inlet Air Heating and Cooling System - A heating and cooling system for inlet air of a turbine compressor. The heating and cooling system may include a fluid coil positioned about the turbine compressor and a thermal energy storage tank. The fluid coil and the thermal energy storage tank are in fluid communication such that fluid is both provided to the fluid coil from the thermal energy storage tank for exchanging heat with the inlet air and returned to the thermal energy storage tank without further heat exchange. | 06-17-2010 |
20100146977 | Deep Chilled Air Washer - A deep chilled air washer for a gas turbine compressor. The deep chilled air washer may include one or more spray arrays for chilling an inlet air stream and one or more drift eliminators positioned downstream of the spray arrays. The drift eliminators may include a heating element therein so as to reheat the inlet air stream. | 06-17-2010 |
20110088399 | Combined Cycle Power Plant Including A Refrigeration Cycle - A method and system for augmenting the output of a combined cycle power plant having a gas turbine driving a generator, a heat recovery steam generator that recovers exhaust heat from the gas turbine to drive a steam turbine also driving a generator, and a refrigeration element that is powered by available energy in steam exhausted from the steam turbine to cool water. The refrigeration element employs a substantially closed cycle refrigeration system that, in a preferred embodiment, is either an absorption chilling system or a thermal compression chilling system. The refrigeration element provides cool water to an inlet chiller arranged to chill inlet to the gas turbine to augment the power output of the gas turbine and the water is recirculated to be chilled and used again. Since the refrigeration cycle is substantially closed, little or no additional plant water consumption is imposed on the power plant. | 04-21-2011 |
20140013757 | Solar Thermal Gas Turbine System - An object of the present invention is to provide a solar thermal gas turbine system enhanced in resistance to effects of disturbances including weather conditions in a gas turbine which sprays water into intake air of a compressor. | 01-16-2014 |
20140047844 | GAS TURBINE ENGINE COMPONENT HAVING PLATFORM TRENCH - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench. | 02-20-2014 |
20140060057 | METHOD AND APPARATUS FOR HEATING LIQUID FUEL SUPPLIED TO A GAS TURBINE COMBUSTOR - A method of heating liquid fuel upstream of a combustor in a system where compressor discharge air is cooled before being supplied to fuel nozzles in the combustor includes the steps of passing the compressor discharge air through a heat exchanger in heat exchange relationship with the liquid fuel to heat the liquid fuel and cool the compressor discharge air; supplying the heated liquid fuel and the cooled compressor discharge air to the combustor. | 03-06-2014 |
20140060058 | GAS TURBINE SYSTEM HAVING AN EVAPORATIVE COOLER - A gas turbine system includes a compressor; a combustion chamber; a gas turbine; and an evaporative cooler. The evaporative cooler includes a plurality of cooling elements, a flow channel, and a feed device. The plurality of cooling elements are arranged in the flow channel. The feed device supplies a liquid to the plurality of cooling elements. The liquid is evaporated or vaporized. Each of the plurality of cooling elements is a flat cooling sheet, a surface of the cooling sheet having hydrophilic properties at least in a subregion which is specified for forming a liquid film. The evaporative cooler is connected ahead of the compressor on an intake side. | 03-06-2014 |
20140109580 | PART LOAD PERFORMANCE IMPROVEMENT USING DEFORMABLE BORE PLUGS - A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy. | 04-24-2014 |
20140144139 | AIR COOLED AIR COOLER FOR GAS TURBINE ENGINE AIR SYSTEM - An air-to-air cooler has a heat exchanger integrated to a housing. A first passage extends through the housing for directing a flow of cooling air through the heat exchanger. A second passage extends through the housing for directing a flow of hot air to be cooled through the heat exchanger. The first passage has a cooling air outlet tube disposed downstream of the heat exchanger. The cooling air outlet tube extends across the second passage between the heat exchanger and a hot air inlet of the second passage. The hot air inlet is disposed to cause incoming hot air to flow over the cooling air outlet tube upstream of the heat exchanger. An ejector drives the flow of cooling air through the first passage of the air-to-air cooler. A portion of the hot air flow may be used to drive the ejector. | 05-29-2014 |
20140216036 | SOLID OXIDE FUEL CELL SYSTEM - A solid oxide fuel cell system ( | 08-07-2014 |
20140290253 | INTAKE AIR COOLING SYSTEM - An intake air cooling system | 10-02-2014 |
20150101334 | HEAT EXCHANGERS - A heat exchanger which may be used in an engine, such as a vehicle engine for an aircraft or orbital launch vehicle. is provided. The heat exchanger may be configured as generally drum-shaped with a multitude of spiral sections, each containing numerous small diameter tubes. The spiral sections may spiral inside one another. The heat exchanger may include a support structure with a plurality of mutually axially spaced hoop supports, and may incorporate an intermediate header. The heat exchanger may incorporate recycling of methanol or other antifreeze used to prevent blocking of the heat exchanger due to frost or ice formation. | 04-16-2015 |
20150121881 | GAS TURBINE INLET SYSTEM AND RELATED METHOD FOR COOLING GAS TURBINE INLET AIR - An inlet air conditioning system for a gas turbine includes an inlet duct for the with an air flow path to provide inlet air to the gas turbine; evaporative cooling media disposed in the air flow path; a water chiller; and a circulation pump that circulates water through the water chiller and the evaporative media in series. The chiller is configured to chill the water to below ambient wet-bulb temperature before the water is circulated to the evaporative cooling media. A power plant includes a gas turbine including a compressor, a combustion system, and a turbine section; a load; and the inlet air conditioning system. | 05-07-2015 |
20160003153 | COOLING AIR SYSTEM FOR AIRCRAFT TURBINE ENGINE - In one aspect, a turbine engine is provided. The engine includes a fan, a core engine case configured to receive a core airflow, and an inner fan case. An inner air bypass is defined between the core engine case and the inner fan case, and the engine further includes an outer fan case, an outer air bypass defined between the inner fan case and the outer fan case, a first heat exchanger arranged in the core engine case, the first heat exchanger providing heat exchange between the liquid and the core airflow to cool the core airflow, and a second heat exchanger arranged in the outer air bypass. The second heat exchanger is fluidly coupled to the first heat exchanger to receive the cooled core airflow. The second heat exchanger provides heat exchange between cooled core airflow and the second portion of airflow to further cool the cooled core airflow. | 01-07-2016 |
20190145316 | Cooled Cooling Air System Having Shutoff Valve and Propulsor | 05-16-2019 |