38th week of 2014 patent applcation highlights part 11 |
Patent application number | Title | Published |
20140260254 | Steam Turbine Power Plant - A steam turbine power plant includes heat-source equipment that heats a low-temperature flow by applying a heat medium and thus generates a high-temperature flow, a steam generator using the high-temperature flow generated by the heat-source equipment, a steam turbine driven by the steam generated by the steam generator, an electric generator that converts rotational motive power of the steam turbine into electric power, a heat-medium controller that controls a supply rate of the heat medium supplied to the heat source equipment, a low-temperature flow controller that controls a supply rate of the low-temperature flow supplied to the heat-source equipment, a prediction device that predicts startup constraints of the steam turbine from control input variables of the controllers when the steam turbine is started, and a control input variables setter so as to prevent data predictions by the prediction device from exceeding limit values of startup constraints. | 2014-09-18 |
20140260255 | SHIP CAPABLE OF RUNNING SELECTIVELY WITH LIQUEFIED FUEL GAS MAIN DRIVE ENGINE AND LIQUEFIED FUEL GAS GENERATOR ENGINE - A ship includes: a high-pressure injection engine using fuel gas as fuel to obtain a propulsion power of the ship; a generator engine using fuel gas as fuel to generate electricity; a motor generating a power by using the electricity generated from the generator engine; a propulsion propelling the ship; a main clutch connecting the high-pressure injection engine to the propulsion; an auxiliary clutch connecting the gear box to the propulsion; and a gear box disposed in a front side of the propulsion and power-connected to the main clutch and the auxiliary clutch. The high-pressure injection engine and the motor are selectively power-connected to the propulsion to obtain the propulsion power of the ship. | 2014-09-18 |
20140260256 | CHECK VALVE FOR PROPULSIVE ENGINE COMBUSTION CHAMBER - A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate. | 2014-09-18 |
20140260257 | ANNULAR WALL OF A COMBUSTION CHAMBER WITH IMPROVED COOLING AT THE LEVEL OF PRIMARY AND/OR DILUTION HOLES - An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall. | 2014-09-18 |
20140260258 | SYSTEM FOR PROVIDING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber disposed downstream from the fuel nozzle, an inner flow sleeve that circumferentially surrounds the combustion chamber and a plurality of injectors circumferentially arranged around the inner flow sleeve. The plurality of injectors provide for fluid communication through the inner flow sleeve and into the combustion chamber downstream from the fuel nozzle. The system further includes an outer air shield that defines an injection air plenum that surrounds the plurality of injectors. An inlet passage extends through the outer air shield to define a flow path into the injection air plenum. An outer sleeve is slidingly engaged with the outer air shield. The outer sleeve has a first position that restricts flow through the inlet passage and a second position that increases flow through the inlet passage. | 2014-09-18 |
20140260259 | MULTI-ZONE COMBUSTOR - A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section. | 2014-09-18 |
20140260260 | COMBUSTOR FOR GAS TURBINE ENGINE - A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber. | 2014-09-18 |
20140260261 | TURBOMACHINE WITH TRANSITION PIECE HAVING DILUTION HOLES AND FUEL INJECTION SYSTEM COUPLED TO TRANSITION PIECE - A turbomachine is provided and includes a combustor in which fuel and air are combusted, a turbine disposed for reception of products of combustion from the combustor, a transition piece fluidly interposed between the combustor and the turbine and including a body formed to define dilution holes configured to allow air to enter the combustor and for enabling steam injection toward a main flow of the products of the combustion proceeding from the combustor to the turbine and a fuel injection system supportively coupled to the transition piece and configured to inject fuel toward the main flow of the products of the combustion to thereby restore a flame temperature of the main flow of the products of the combustion reduced by steam injection enabled by the dilution holes. | 2014-09-18 |
20140260262 | SYSTEMS AND APPARATUS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A gas turbine that includes: a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a primary air and fuel injection system that defines a forward end, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end; and a downstream injection system that includes two injection stages, a first stage and a second stage, that are axially spaced along the longitudinal axis of the interior flowpath. The first stage and the second stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath. | 2014-09-18 |
20140260263 | FUEL INJECTION INSERT FOR A TURBINE NOZZLE SEGMENT - One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit. | 2014-09-18 |
20140260264 | SYSTEM FOR CONTROLLING A FLOW RATE OF A COMPRESSED WORKING FLUID TO A COMBUSTOR FUEL INJECTOR - A system for controlling air flow rate of a compressed working fluid to a fuel injector of a combustor includes an outer casing that defines a high pressure plenum around a portion of the combustor, an extraction port in fluid communication with the high pressure plenum and an inlet port. The combustor includes a plurality of fuel injectors arranged around a combustion liner, an inner flow sleeve, an outer air shield that surrounds the plurality of fuel injectors and the inner flow sleeve. The outer air shield defines an injection an air plenum between the outer air shield and the inner flow sleeve and an inlet to the injection air plenum. An external fluid circuit provides fluid communication between the extraction port and the inlet port. A baffle extends between the outer casing and the outer air shield to provide flow separation between the inlet and the high pressure plenum. | 2014-09-18 |
20140260265 | COMBUSTION CHAMBER FOR A GAS TURBINE AND BURNER ARRANGEMENT - A combustion chamber ( | 2014-09-18 |
20140260266 | COMBUSTOR FOR GAS TURBINE ENGINE - A gas turbine engine comprises an annular combustor chamber formed between an inner liner and an outer liner. An annular upstream zone is adapted to receive fuel and air from an annular nozzle. An annular mixing zone is located downstream of the upstream zone. The mixing zone has a reduced radial height relative a downstream combustion zone of the combustion chamber, the mixing zone defined by straight wall sections. | 2014-09-18 |
20140260267 | COMBUSTOR END COVER WITH FUEL PLENUMS - A system includes a system having an end cover of a combustor for a gas turbine. The end cover has at least one fuel plenum coupled to a plurality of fuel injectors for a multi-tube fuel nozzle having a plurality of fuel-air mixing tubes, each tube having one of the fuel injectors. At least one fuel plenum is configured to provide fuel to each of the fuel injectors. | 2014-09-18 |
20140260268 | MICROMIXING CAP ASSEMBLY - A system includes a combustor cap assembly for a multi-tube fuel nozzle. The combustor cap assembly includes a support structure defining an interior volume configured to receive an air flow, a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector and is individually removable from the combustor cap assembly, an air distributor disposed within the interior volume and configured to distribute the air flow received by the interior volume to each of the plurality of mixing tubes, and a combustor cap removably coupled to the support structure. | 2014-09-18 |
20140260269 | SYSTEMS AND APPARATUS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A gas turbine engine that includes: a combustor coupled to a turbine and a downstream injection system that includes two injection stages, a first stage and a second stage, positioned within an interior flowpath, wherein the first stage comprises an axial position that is aft of the primary air and fuel injection system and the second stage comprising an axial position that is aft of the first stage. Each of the first stage and the second stage include a plurality of circumferentially spaced injectors, each injector of which is configured to inject air and fuel into a flow through the interior flowpath. The first stage and the second stage have a configuration that limits a fuel injected at the second stage to less than 50% of a fuel injected at the first stage. | 2014-09-18 |
20140260270 | SYSTEMS AND APPARATUS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A gas turbine engine that includes: an interior flowpath defined through a combustor and a turbine; an aft frame forming an interface between the combustor the turbine, the aft frame comprising a rigid structural member that circumscribes the interior flowpath, wherein the aft frame includes an inner wall that defines an outboard boundary of the interior flowpath; a circumferentially extending fuel plenum formed through the aft frame; and outlet ports formed through the inner wall of the aft frame. The outlet ports may be configured to connect the fuel plenum to the interior flowpath. | 2014-09-18 |
20140260271 | System Having a Multi-Tube Fuel Nozzle - A system including a plurality of multi-tube fuel nozzles each having a plurality of tubes extending in an axial direction, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, a fuel nozzle housing including a first outer wall extending circumferentially about a central axis, wherein the plurality of multi-tube fuel nozzles are disposed in the fuel nozzle housing, an inlet flow conditioner removably coupled to a first end portion of the first outer wall, wherein the inlet flow conditioner includes a plurality of air openings, and an aft plate assembly removably coupled to a second end portion of the first outer wall, wherein the aft plate assembly includes an aft plate having a plurality of tube apertures, and the plurality of tubes extend to the plurality of tube apertures. | 2014-09-18 |
20140260272 | SYSTEM FOR PROVIDING FUEL TO A COMBUSTOR - A system for providing fuel to a combustor of a gas turbine includes an annular fuel distribution manifold that at least partially defines a fuel plenum. The fuel distribution manifold includes a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange. A LLI assembly extends downstream from the fuel distribution manifold. The LLI assembly includes a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone within the combustor. A LLI injector extends substantially radially through the unibody liner and provides for fluid communication through the unibody liner into the secondary combustion zone. A fluid conduit in fluid communication with the fuel plenum extends between the LLI injector and the fuel distribution manifold. | 2014-09-18 |
20140260273 | CONTINUOUS COMBUSTION LINER FOR A COMBUSTOR OF A GAS TURBINE - A combustion liner for a gas turbine combustor includes an annular main body having a forward end axially separated from an aft end, and a transitional intersection defined between the forward end and the aft end. The main body extends continuously from the forward end to the aft end. A plurality of fuel injector passages extend radially through the main body upstream from the transitional intersection. The main body comprises a conical section having a circular cross section that diverges between the forward end and the transitional intersection, and a transition section having a non-circular cross section that extends from the transitional intersection to the aft end of the main body. | 2014-09-18 |
20140260274 | FUEL DISTRIBUTION MANIFOLD FOR A COMBUSTOR OF A GAS TURBINE - A fuel distribution manifold for a combustor of a gas turbine includes an annular flange having an outer surface that extends circumferentially around the flange. A primary fuel plenum extends circumferentially within the flange. A first orifice and a second orifice extend radially through the outer surface of the flange to provide for fluid communication into the primary fuel plenum. The first orifice includes an inlet that is adjacent to the outer surface. The second orifice includes an inlet that is adjacent to the outer surface. A fuel distribution cap extends partially across the outer surface of the flange. The fuel distribution cap includes an inlet port. A fuel distribution plenum is at least partially defined within the fuel distribution cap. The fuel distribution plenum is in fluid communication with the inlet port and with the first orifice inlet and the second orifice inlet. | 2014-09-18 |
20140260275 | FLOW SLEEVE ASSEMBLY FOR A COMBUSTION MODULE OF A GAS TURBINE COMBUSTOR - A flow sleeve assembly for a combustor of a gas turbine includes an annular support sleeve disposed at a forward end of the flow sleeve assembly. The support sleeve includes a forward portion axially separated from an aft portion. An aft frame is disposed at an aft end of the flow sleeve assembly. An annular flow sleeve extends from the aft portion of the support sleeve towards the aft frame. The flow sleeve includes a forward end that is axially separated from an aft end. The forward end of the flow sleeve circumferentially surrounds the aft end of the support sleeve. An annular impingement sleeve extends between the aft end of the flow sleeve and the aft frame. A forward end of the impingement sleeve is connected to the aft end of the flow sleeve, and an aft end of the impingement sleeve is connected to the aft frame. | 2014-09-18 |
20140260276 | END COVER CONFIGURATION AND ASSEMBLY - A system includes an end cover for a multi-tube fuel nozzle. The end cover includes a first side, a second side disposed opposite the first side, a plurality of fuel injectors disposed on the first side, and at least one pre-orifice disposed within a passage within the end cover between the first and second sides. The pre-orifice is configured to be removed through the end cover from the second side. | 2014-09-18 |
20140260277 | FLOW SLEEVE FOR A COMBUSTION MODULE OF A GAS TURBINE - A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve. | 2014-09-18 |
20140260278 | SYSTEM FOR TUNING A COMBUSTOR OF A GAS TURBINE - A system for tuning a combustor of a gas turbine includes a flow sleeve having an annular main body. The main body includes an upstream end, a downstream end, an inner surface and an outer surface. A cooling channel extends along the inner surface of the main body. The cooling channel extends at least partially between the downstream end and the upstream end of the main body. | 2014-09-18 |
20140260279 | HOT GAS PATH DUCT FOR A COMBUSTOR OF A GAS TURBINE - A hot gas path duct or unibody liner for a gas turbine includes a main body having a forward end and an aft end. The main body defines a cross-sectional flow area and an axial flow length that extends between the forward end and the aft end. The main body further defines a fuel injection portion disposed downstream from the forward end and upstream from the aft end. The cross-sectional flow area decreases along the axial flow length between the forward end and the fuel injection portion and increases along at least a portion of the axial flow length downstream from the fuel injection portion. | 2014-09-18 |
20140260280 | ASSEMBLY FOR CONTROLLING CLEARANCE BETWEEN A LINER AND STATIONARY NOZZLE WITHIN A GAS TURBINE - An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell. | 2014-09-18 |
20140260281 | AUXETIC STRUCTURE WITH STRESS-RELIEF FEATURES - A material which exhibits auxetic characteristics and control of thermal expansion characteristics while experiencing significant stress reduction is disclosed. The material has a repeating pattern of void structures along both lateral symmetry lines and longitudinal symmetry lines. | 2014-09-18 |
20140260282 | GAS TURBINE ENGINE COMBUSTOR LINER - A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages. | 2014-09-18 |
20140260283 | GAS TURBINE ENGINE EXHAUST MIXER WITH AERODYNAMIC STRUTS - An exhaust mixer for a gas turbine engine has a plurality of circumferentially distributed alternating inner and outer lobes, and a plurality of aerodynamic struts positioned and oriented between adjacent inner lobes in the core flow passage. The struts are configured for diverting a portion of the core flow radially outwardly in troughs formed by the outer lobes on the core flow side of the mixer. | 2014-09-18 |
20140260284 | System and Method for Loading a Combined Cycle Power Plant - A system including a gas turbine system configured to transition between a first load state and a second load state, wherein the gas turbine system comprises an airflow control module configured to adjust an airflow through the gas turbine system between a minimum airflow condition and a maximum airflow condition, and a controller configured to control the gas turbine system to operate with a load path between a first load path corresponding to the minimum airflow condition and a second load path corresponding to the maximum airflow condition, wherein the controller is configured to control the gas turbine system to transition between the first load state and the second load state using the load path between the first and second load paths. | 2014-09-18 |
20140260285 | Gas-to-Liquid Heat Exchange System with Multiple Liquid Flow Patterns - Systems and methods for the design of a heat recovery steam generator (HRSG) or similar system that is designed to extract heat from hot gases flowing through a duct which utilizes an external liquid-to-liquid heat exchanger for preheating feedwater. The systems and methods allow for multiple water flow patterns to adjust the temperature of the feedwater into the gas duct. | 2014-09-18 |
20140260286 | LOCALIZED FLUE GAS DILUTION IN HEAT RECOVERY STEAM GENERATOR - A heat recovery steam generator (HRSG) ( | 2014-09-18 |
20140260287 | GAS TURBINE FIRING TEMPERATURE OPTIMIZATION BASED ON SULFUR CONTENT OF FUEL SUPPLY - Gas turbine firing temperature optimization based on a measured sulfur content of a fuel supply of the gas turbine system is provided. In one embodiment, a system includes a diagnostic system configured to determine a maximum firing temperature for a combustor of a gas turbine system. The diagnostic system may determine the maximum firing temperature based on a predetermined sulfur content to maximum firing temperature correlation and an actual sulfur content of a fuel supplied to the combustor. The diagnostic system may also be configured to provide an indicator for a change in an actual firing temperature in the combustor of the gas turbine system. The diagnostic system may provide the indicator in response to the determined maximum firing temperature differing from the actual firing temperature of the combustor of the gas turbine system. | 2014-09-18 |
20140260288 | SYSTEM AND METHOD FOR START-UP OF A COMBINED CYCLE POWER PLANT - In accordance with one aspect of the present technique, a method is disclosed. The method includes modifying one or more operational parameters of a gas turbine (GT) to increase an exhaust gas temperature above a standard start-up temperature. The method also includes receiving at least one of GT operational data, heat recovery steam generator (HRSG) operational data, and steam turbine (ST) operational data from a plurality of sensors. The method further includes predicting a ST roll-off time based on at least one of the GT operational data, the HRSG operational data, and the ST operational data. The method further includes modifying the one or more operational parameters of the GT to satisfy one or more ST roll-off permissives at the predicted ST roll-off time. | 2014-09-18 |
20140260289 | MULTI-PASSAGE DIFFUSER WITH REACTIVATED BOUNDARY LAYER - A diffuser is disclosed that includes a splitter having a blunt forebody useful in re-starting a boundary layer. The blunt forebody can be used to create a static pressure bow wave and interaction with a passing fluid stream that reduces a thickness of boundary layer formed on an opposing wall. The re-start in boundary layer can be used in a way that allows an upstream portion of the diffuser to be sized approaching a separation limit and a downstream portion of the diffuser to also be sized approaching a separation limit. In some forms the passages split by the blunt forebody can be sized relative to each other to balance flow between the branches. | 2014-09-18 |
20140260290 | POWER-GENERATING APPARATUS AND METHOD - A power-generating apparatus includes a compressor section and a combustor section positioned downstream of the compressor section. The combustor section defines a combustion chamber operable to receive compressed fluid from the compressor section. The apparatus includes a turbine section positioned downstream of the combustor section operable to receive combustion gases from the combustion chamber and convert the combustion gases into kinetic energy. The apparatus also includes a waste container positioned downstream of the turbine section and exposed to the discharged exhaust gases. The waste container can hold waste material that receives the hot exhaust gas and combusts, further heating the exhaust gases. The apparatus also includes a conduit having an inlet fluidly communicating with the turbine section and receiving the exhaust gases. The apparatus also includes a heat exchanger operably disposed between the compressor section and the combustor section to heat the compressed fluid. | 2014-09-18 |
20140260292 | GAS TURBINE AND METHOD FOR GUIDING COMPRESSED FLUID IN A GAS TURBINE - A gas turbine having a combustion chamber with exhaust section through which combustion gas is exhaustable, plenum chamber and compressor are provided. The plenum chamber is coupled to the compressor wherein a first quantity of compressed fluid is injectable therein at a radially inner wall of the plenum chamber. A guide vane section with at least one airfoil is coupled to the exhaust section so combustion gas is flowable against the airfoil. The exhaust section and guide vane section are housed inside the plenum chamber. The airfoil has a first flow chamber where a second quantity of compressed fluid is flowable through the guide vane section from the compressor in the direction from the inner wall to a outer wall of the plenum chamber before being discharged. The second quantity of compressed fluid streamable through the guide vane section is larger than the first quantity of the compressed fluid. | 2014-09-18 |
20140260293 | SYSTEMS AND METHODS OF DROOP RESPONSE CONTROL OF TURBINES - A system includes a controller configured to control an operational behavior of a turbine system. The controller includes a droop response system configured to detect one or more operational characteristics of the turbine system as an indication of a frequency variation of an electric power system associated with the turbine system. The droop response system is further configured to generate a response to vary an output of the turbine system in response to the indication of the frequency variation. The controller includes a multivariable droop response correction system configured to determine one or more possible errors associated with the one or more operational characteristics of the turbine system, and to generate a plurality of correction factors to apply to the response generated by the droop response system. The plurality of correction factors is configured to correct the response generated by the droop response system. | 2014-09-18 |
20140260294 | Apparatus and Method for Controlling a Pressure Gain Combustor - A method of controlling operation of a pressure gain combustor comprises: determining a fuel injector duty cycle and a combustion frequency that meets a target load set point and a target fill fraction of the combustor; determining a fuel supply pressure setting, a fuel injector timing setting and an ignition timing setting that achieves the determined fuel injector duty cycle and combustion frequency; and sending a fuel supply pressure control signal with the fuel supply pressure setting to a fuel pressurizing means of the combustor, a fuel injector control signal with the fuel injector timing setting to a fuel injector of the combustor, and an ignition timing control signal with the ignition timing setting to an ignition assembly of the combustor. | 2014-09-18 |
20140260295 | GAS TURBINE ENGINE WITH TRANSMISSION AND METHOD OF ADJUSTING ROTATIONAL SPEED - A method of adjusting a rotational speed of the low pressure compressor rotor(s) of a gas turbine engine, including rotating the high pressure compressor rotor(s) with the high pressure turbine rotor(s) through the high pressure spool, rotating the low pressure turbine rotor(s) with a flow of exhaust gases from the high pressure turbine, rotating the low pressure spool with the low pressure turbine rotor(s), rotating a load of the engine with the low pressure spool, driving a rotation of the low pressure compressor rotor(s) with the low pressure spool through a variable transmission defining a variable transmission ratio between rotational speeds of the compressor rotor(s) and the low pressure spool, and adjusting the transmission ratio to obtain a desired rotational speed for the low pressure compressor rotor(s). A method of adjusting rotational speeds of a gas turbine engine and a gas turbine engine are also described. | 2014-09-18 |
20140260296 | SLINGER COMBUSTOR - A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion chamber has a fuel atomization zone extending radially outwardly from the fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone. A plurality of nozzle air inlets are defined in the fuel atomization zone of the combustor shell. The nozzle air inlets have a nozzle axis intersecting the stream of fuel and a tangential component in a direction of rotation of the fuel slinger. A plurality of dilution holes are defined in the combustor shell and have a dilution axis intersecting the combustion zone. The dilution axis of at least some of the dilution holes has a tangential component opposite to the direction of rotation of the fuel slinger. | 2014-09-18 |
20140260297 | COMBUSTOR FOR GAS TURBINE ENGINE - A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber. | 2014-09-18 |
20140260298 | COMBUSTOR FOR GAS TURBINE ENGINE - A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber. | 2014-09-18 |
20140260299 | FUEL-AIR MIXING SYSTEM FOR GAS TURBINE SYSTEM - Embodiments of the present disclosure are directed to systems and methods for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of fuel injectors and a plurality of mixing tubes, wherein each mixing tube has a first portion for receiving one of the plurality of fuel injectors and a second portion having a mixing chamber that is configured to mix fuel and air. The length of the mixing chamber varies among the plurality of mixing tubes to allow for different mixing times. | 2014-09-18 |
20140260300 | AIR DIFFUSER FOR COMBUSTOR - A system includes a multi-tube fuel nozzle of a turbine combustor. The multi-tube fuel nozzle includes a support structure defining an interior volume configured to receive an air flow; a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector; and an outer annular wall configured to direct an air flow from an annulus between a liner and a flow sleeve of the turbine combustor at least partially radially inward into the interior volume through an air inlet and toward the plurality of mixing tubes, wherein the outer annular wall at least partially defines an air flow passage extending from the annulus to the interior volume. | 2014-09-18 |
20140260301 | ENGINE MANIFOLD DRAIN SYSTEM - A fuel system for a gas turbine engine includes an engine fuel manifold, a hydraulic actuator, and a drain piston assembly. The hydraulic actuator actuates in response to a change in pressures within the hydraulic actuator. The drain piston assembly is fluidically connected to both the hydraulic actuator and the engine fuel manifold. The drain piston assembly receives fuel from the engine fuel manifold and sends fuel to the hydraulic actuator during engine shut down. | 2014-09-18 |
20140260302 | DIFFUSION COMBUSTOR FUEL NOZZLE FOR LIMITING NOx EMISSIONS - The present application and the resultant patent provide a diffusion combustor fuel nozzle for a gas turbine engine. The fuel nozzle may include one or more gas fuel passages for one or more flows of gas fuel, a swirler surrounding the one or more gas fuel passages and positioned about a downstream face of the fuel nozzle, a number of swirler gas fuel ports defined in the swirler, and a number of downstream face gas fuel ports defined in the downstream face of the fuel nozzle. The swirler may include a number of swirl vanes and a number of air chambers defined between adjacent swirl vanes. The present application and the resultant patent further provide a method of operating a diffusion combustor fuel nozzle of a gas turbine engine. | 2014-09-18 |
20140260303 | METHODS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A method for use in a gas turbine engine. The method includes the steps of: configuring a downstream injection system within the interior flowpath that includes two injection stages, a first stage and a second stage, wherein the first stage and the second stage are each axially spaced from the other; and circumferentially positioning the injectors of the first stage and the second stage based on: a) a characteristic of an anticipated combustion flow occurring just upstream of the first stage during a mode of operation; and b) the characteristic of an anticipated combustion flow just downstream of the second stage given an anticipated effect of the air and fuel injection from the first stage and the second stage. | 2014-09-18 |
20140260304 | ALGAE-DERIVED FUEL/WATER EMULSION - A method including providing a wet algae material having been subjected to a refinement process without a water separation phase; supplying the wet algae material including a water fraction and an algae-grown biofuel to a turbine engine; and operating the turbine engine with the wet algae material where a retained portion of the water fraction is retained in the wet biofuel during a manufacturing process not including a dehydration step and includes an amount sufficient to reduce generation of a quantity of nitrogen oxides, and where the turbine engine can further include a combustor capable of combusting the wet biofuel. | 2014-09-18 |
20140260305 | LEAN AZIMUTHAL FLAME COMBUSTOR - A combustion chamber may include a first surface and a second surface interconnected by a wall forming a chamber having a central axis. The first surface may define an exhaust opening and the second surface defining a pilot opening, wherein the exhaust opening and the pilot opening align along the central axis. A plurality of inlet ports may be configured to deliver air to the chamber. A plurality of fuel ports may be arranged on an inside of the second surface to deliver fuel to the chamber. The air flow from the inlet ports and fuel from the fuel ports may oppose each other to create a vortex of product proximal to the second surface. | 2014-09-18 |
20140260306 | ENGINE STARTING SYSTEM USING STORED ENERGY - There is described a method for and system for starting at least one engine from a twin engine installation. The starting system comprises a first engine arrangement comprising a first electric machine having a single rotor dual stator configuration, a first dual channel power control unit coupled to the first electric machine, and a first dual channel full authority digital engine control (FADEC) coupled to the first dual channel power control unit; a second engine arrangement comprising a second electric machine having a single rotor dual stator configuration, a second dual channel power control unit coupled to the second electric machine, and a second dual channel full authority digital engine control (FADEC) coupled to the second dual channel power control unit; an energy storage unit coupled to the first engine arrangement and the second engine arrangement and having at least a first super-capacitor and a second super-capacitor; and a DC to DC converter configured to receive a first voltage level from a power source, increase the first voltage level to a second voltage level, and charge the first super-capacitor and the second super-capacitor to the second voltage level. | 2014-09-18 |
20140260307 | REAR MOUNTED WASH MANIFOLD AND PROCESS - An engine wash manifold delivers wash liquid to an engine that includes an inlet, a fan, a case with an exhaust duct and a core inlet splitter. The manifold includes a wash delivery segment comprising a pipe shaped to follow at least in part engine case curvature with a first end to interface with the core inlet splitter and a second end with an inlet to receive wash fluid. The manifold further includes a retention system to secure the wash delivery segment to the engine and one or more nozzles on the first end of the wash delivery segment to spray wash fluid. The wash fluid may be atomized. The manifold further may include nozzles that deliver atomized wash liquid to the aft side of fan blades and may be used in conjunction with an inlet mounted manifold. | 2014-09-18 |
20140260308 | REAR MOUNTED WASH MANIFOLD RETENTION SYSTEM - A retention system includes a structure clamp to connect the retention system to another structure; and a manifold clamp connected to the structure clamp, the manifold clamp including a trough to receive a pipe, a plurality of tube clamps with split cylinders extending through the trough, a collar to clamp around the pipe, and a spring to bias the trough from the collar. | 2014-09-18 |
20140260309 | SYSTEM AND METHOD FOR FUEL BLENDING AND CONTROL IN GAS TURBINES - A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel. | 2014-09-18 |
20140260310 | Integrated Power Generation Using Molten Carbonate Fuel Cells - In various aspects, systems and methods are provided for integrated operation of molten carbonate fuel cells with turbines for power generation. Instead of selecting the operating conditions of a fuel cell to improve or maximize the electrical efficiency of the fuel cell, an excess of reformable fuel can be passed into the anode of the fuel cell to increase the chemical energy output of the fuel cell. The increased chemical energy output can be used for additional power generation, such as by providing fuel for a hydrogen turbine. | 2014-09-18 |
20140260311 | Integration of Molten Carbonate Fuel Cells with Fermentation Processes - In various aspects, systems and methods are provided for operating a molten carbonate fuel cell assembly at increased power density. This can be accomplished in part by performing an effective amount of an endothermic reaction within the fuel cell stack in an integrated manner. This can allow for increased power density while still maintaining a desired temperature differential within the fuel cell assembly. | 2014-09-18 |
20140260312 | SYSTEMS AND METHODS FOR GAS TURBINE TUNING AND CONTROL - A method of tuning a gas turbine includes receiving a first plurality of operating parameters as the gas turbine engine is operated at a first operating state. Further, the method includes operating the gas turbine engine at a second operating state to measure a second plurality of operating parameters at the second operating state. In addition, the method includes operating the gas turbine engine at a third operating state to measure a third plurality of operating parameters at the third operating state, wherein the first, second, and third operating states are different from each other. Additionally, the method includes generating a correction factor based on the first, second, and third plurality of operating parameters. The method also includes adjusting the operation of the gas turbine engine based on the correction factor. | 2014-09-18 |
20140260313 | MICRO-MIXER/COMBUSTOR - A micro-mixer/combustor to mix fuel and oxidant streams into combustible mixtures where flames resulting from combustion of the mixture can be sustained inside its combustion chamber is provided. The present design is particularly suitable for diffusion flames. In various aspects the present design mixes the fuel and oxidant streams prior to entering a combustion chamber. The combustion chamber is designed to prevent excess pressure to build up within the combustion chamber, which build up can cause instabilities in the flame. A restriction in the inlet to the combustion chamber from the mixing chamber forces the incoming streams to converge while introducing minor pressure drop. In one or more aspects, heat from combustion products exhausted from the combustion chamber may be used to provide heat to at least one of fuel passing through the fuel inlet channel, oxidant passing through the oxidant inlet channel, the mixing chamber, or the combustion chamber. In one or more aspects, an ignition strip may be positioned in the combustion chamber to sustain a flame without preheating. | 2014-09-18 |
20140260314 | Variable Heat/Power Ratio Cogeneration System - A variable heat/power ratio cogeneration system is provided that is capable of suppressing NOx emissions to a minimum while ensuring stability of combustion of a gas turbine combustor even when the ratio of gasification gas to normal fuel (e.g., natural gas or light fuel oil) to be used is changed or the composition of the gasification gas fuel is changed. The system includes a first steam system injecting extra steam upstream of the flame zone; a second steam system branched from the first system and injecting extra steam downstream of the flame zone; first and second steam flow rate control valves controlling steam injected by first and steam systems, respectively; and a controller that controls first and second control valves based on (1) flow rates of the gasification gas and normal fuel and (2) demanded steam. | 2014-09-18 |
20140260315 | SYSTEM HAVING MULTI-TUBE FUEL NOZZLE WITH FLOATING ARRANGEMENT OF MIXING TUBES - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes an end cover, a first plate, and multiple tubes. The multiple tubes are disposed and supported in a floating arrangement between the end cover and the first plate. Each tube includes a forward end adjacent the end cover and an aft end adjacent the first plate. | 2014-09-18 |
20140260316 | GAS TURBINE TRANSITION INLET RING ADAPTER - A combustion system for a gas turbine engine including a combustor assembly comprising a combustor basket having a downstream terminal end, and a transition duct extending downstream from the combustor basket and having an upstream end located adjacent to the downstream terminal end of the combustor basket. A coupling is provided comprising an inlet ring adapter including a cylindrical sleeve extending downstream of the upstream end of the transition duct in overlapping relation to an inner surface of the transition duct. A spring clip assembly is mounted to the terminal end of the combustor basket. The spring clip assembly extends into engagement with and forms a seal on the cylindrical sleeve. | 2014-09-18 |
20140260317 | GAS TURBINE COMBUSTOR EXIT PIECE WITH HINGED CONNECTIONS - An exit piece ( | 2014-09-18 |
20140260318 | SIDE SEAL SLOT FOR A COMBUSTION LINER - A side seal slot extends along a one side of an aft frame for a combustion liner of a gas turbine. The side seal slot is at least partially defined between a downstream wall and an upstream wall that extend outward from the first side of the aft frame. A first segment of the upstream wall extends from an inner portion of the aft frame towards an outer portion of the aft frame at a first outward distance from the first side. A second segment of the upstream wall extends from the first segment to the outer portion of the aft frame at a second outward distance from the first side. The second segment of the upstream wall at least partially defines a side seal guide feature to allow for axial insertion of a bottom portion of a side seal into the side seal slot. | 2014-09-18 |
20140260319 | COMBUSTOR SUPPORT ASSEMBLY FOR MOUNTING A COMBUSTION MODULE OF A GAS TURBINE - A gas turbine comprises a compressor discharge casing that is coupled to an outer turbine shell. The compressor discharge casing includes a combustor opening that extends through the compressor discharge casing and an outer mating surface that circumferentially surrounds the combustor opening. The outer turbine shell defines an inner mating surface. A combustion module extends through the combustor opening. The combustion module includes a forward end that is circumferentially surrounded by a mounting flange and an aft end that is circumferentially surrounded by an aft frame. The mounting flange extends circumferentially around the combustor opening. The mounting flange is coupled to the outer mating surface of the compressor discharge casing and the aft frame is coupled to the inner mating surface of the outer turbine shell. | 2014-09-18 |
20140260320 | BI-METAL FASTENER FOR THERMAL GROWTH COMPENSATION - An improved fastening system and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system could employ a metallic fastener that is combined with metallic spacer, each of which having a differing thermal growth coefficient. This arrangement may reduce thermal expansion by several orders of magnitude over the range of temperatures where the thermal fastener can be applied. Such an improved fastening system may be employed in gas turbine machines and in other locations where it is desirable to improve fastening of objects in extreme temperature environments. | 2014-09-18 |
20140260321 | GAS TURBINE ENGINE STATIC STRUCTURE JOINT WITH UNDERCUTS - A gas turbine engine static structure has a joint that includes at least two flanges. The first flange includes a face extending axially proud between radially spaced apart undercuts. The second flange abuts the face. Fasteners secure the flanges to one another through the face. | 2014-09-18 |
20140260322 | SUPPORT MECHANISM FOR HEAVY STRUCTURE - To provide a support mechanism for a heavy structure, capable of accommodating thermal deformation of component parts of a device operated under high temperature condition, a support mechanism for supporting the heavy structure by suspending includes a fast pulley fixed to an inner wall of a package that accommodates the heavy structure which is an object being supported, a movable pulley to function cooperatively with the fast pulley, a rope-like connecting member having one end connected with the structure and movably wound on the fast pulley and the movable pulley, a counterweight unit coupled to the other end of the connecting member and including a counterweight having adjustable weight to utilize the weight of the counterweight to support the heavy structure, and a suspending device in the counterweight unit to suspend and position the heavy structure at a position upwardly relative to a normal support position. | 2014-09-18 |
20140260323 | GAS TURBINE ENGINE AND ACTIVE BALANCING SYSTEM - The present disclosure provides, in one embodiment, a unique gas turbine engine. Other embodiments include unique gas turbine engines, and unique active balancing systems; as well as apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and active balancing systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 2014-09-18 |
20140260324 | TURBO-MACHINERY ROTORS WITH ROUNDED TIP EDGE - A rotor for a gas turbine engine includes a plurality of radially extending blades, each having a remote blade tip defining an outer tip surface, and a leading edge defined between opposed pressure and suction side airfoil surfaces. A shroud circumferentially surrounds the rotor, and a radial distance between an inner surface of the shroud and the outer tip surface of the blades defines a radial tip clearance gap therebetween. The tip of each of the blades has a pressure side edge formed at the intersection between the outer tip surface and the pressure side airfoil surface, and a suction side edge formed at the intersection between the outer tip surface and the pressure side airfoil surface. The suction side edge has a larger radius of curvature than the pressure side edge, thereby reducing the amount of tip leakage flow through the radial tip clearance gap. | 2014-09-18 |
20140260325 | GAS TURBINE ENGINE EXHAUST FLUID PASSAGE DUCT - A fluid plenum including a body defining an internal cavity having an inlet and an outlet. The fluid plenum further includes at least one wall positioned in the internal cavity that divides the internal cavity into first and second passageways, and which also divides the inlet into first and second inlet portions, and divides the outlet into first and second outlet portions. The first passageway receives fluid through the first inlet portion and directs fluid to the first outlet portion, and the second passageway receives fluid through the second inlet portion and directs fluid to the second outlet portion. The first and second passageways extend first and second lengths that are different from one another, and also generate a substantially common back-pressure at the first and second inlet portions during flow of a fluid stream through the inlet, including a first sub-stream of the fluid stream through the first passageway and a second sub-stream of the fluid stream through the second passageway. | 2014-09-18 |
20140260326 | GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE - A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000° F. and about 1500° F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis. | 2014-09-18 |
20140260327 | COOLED ARTICLE - The present invention is an article containing internal cooling channels located near at least one surface. In an embodiment, the cooled article includes a base material, a first layer, and a second layer. Here, the first layer is bonded to the base material and the second layer is bonded to the first layer, wherein at least one closed cooling channel is disposed within a portion of the first layer and a portion of the second layer. | 2014-09-18 |
20140260328 | ELECTRONIC APPARATUS AND COOLING METHOD - A system that cools an electric component by a cooling medium cooled by a heat exchanger, the system includes a pipe through which a cooling medium to cool the electronic component flows; a metal member configured to be coupled with an outer surface of the pipe; a Peltier device configured to cool the metal member to a temperature lower than a temperature of the outer surface of the pipe; a detector that detects dew condensation of outer air occurring on the metal member; and a processor that lowers the temperature of the cooling medium, and stops lowering a temperature of cooling medium when the occurrence of dew condensation of outer air on the metal member is detected. | 2014-09-18 |
20140260329 | METHOD AND SYSTEM FOR THERMOELECTRIC COOLING OF PRODUCTS ON DISPLAY AT RETAIL - A thermoelectrically cooled system and method is disclosed, which includes a thermoelectrically cooled sleeve, which is configured to hold one or more cylindrical cans of a retail product. The thermoelectrically cooled sleeve includes an outer cylindrical body, an inner cylindrical body, a thermoelectric element located between the outer cylindrical body and the inner cylindrical body, and at least one pair of electrical leads attachable to the thermoelectrically cooled sleeve, and upon application of a source of electrical power to the pair of electrical leads heat moves through the thermoelectric element from the inner cylindrical body to the outer cylindrical body of the thermoelectrically cooled sleeve. | 2014-09-18 |
20140260330 | Thermoelectric Assembly - A thermoelectric assembly is disclosed, the assembly having a cold side and a hot side, where each of the hot side and cold side comprises a fan sink. Thermoelectric modules may be between the hot side and cold side and arranged in one circuit or multiple parallel circuits, and in direct thermal contact with both the hot side and the cold side. Each of the hot side and cold side has an air intake direction and an exhaust direction. | 2014-09-18 |
20140260331 | DEVICES, SYSTEMS AND METHODS OF COOLING THE SKIN - According to some embodiments, a thermal conditioning system for selectively cooling skin of a subject comprises at least one thermal conditioning device comprising a first side and second side, the second side being generally opposite of the first side. In some embodiments, the system further comprises a heat sink positioned along the second side of the at least one thermal conditioning device, wherein the first side of the at least one thermal conditioning device is configured to be placed in contact with or in close proximity to a skin surface of the subject to selectively cool or heat the skin surface. | 2014-09-18 |
20140260332 | DUAL COOLING SYSTEMS TO MINIMIZE OFF-CYCLE MIGRATION LOSS IN REFRIGERATORS WITH A VACUUM INSULATED STRUCTURE - An appliance that includes a vacuum insulated cabinet structure having an exterior wall and an interior wall with a vacuum therebetween that forms at least the back wall, bottom, right side, left side, and top of the appliance; and a dual cooling system that includes at least one vapor compression system portion configured to operate during a pull down mode and a thermoelectric portion configured to operate in a steady-state mode without the vapor compression system operating while providing sufficient cooling to offset the steady-state heat load of the appliance. | 2014-09-18 |
20140260333 | DIRECT INJECTION PHASE CHANGE TEMPERATURE CONTROL SYSEM - A thermal control unit (TCU) for controlling temperature of a device under test (DUT) includes a sealed evaporation chamber disposed therein, the evaporation chamber configured with a refrigerant inlet and a refrigerant outlet; and at least one surface for thermal engagement of the device under test and configured to conduct heat to the evaporation chamber. A test system and a computer program product are disclosed. | 2014-09-18 |
20140260334 | SECURE THERMOELECTRIC DEVICE - The device includes a thermoelectric module provided with a thermocouple. Said thermocouple includes a first and second leg which are made of different thermoelectric materials, electrically connected by a connecting element configured to deform according to the temperature thereof so as to assume: a first deformation position in which the first and second legs are electrically connected in series solely by means of the connecting element; and a second deformation position in which the connecting element is in electrical contact with a shunt contact pad of the device, said shunt contact pad being made of a material, the electrical conductivity of which is greater than the electric conductivity of the connecting element and of the first and second legs. The device also includes a load, the electrical resistance of which is lower than the electrical resistance of the thermoelectric module, said load being electrically connected to the shunt contact pad. | 2014-09-18 |
20140260335 | Methods and Devices for Drying Hydrocarbon Containing Gas - Processes and devices for recovering natural gas liquid from a hydrocarbon containing gas are provided by introduction of compressed air to a vortex tube. The vortex tube generates a cold air stream that is introduced into a heat exchanger. A hydrocarbon containing gas of higher temperature than the cold air stream is introduced into the heat exchanger, so that the cold air stream in the heat exchanger cools the hydrocarbon containing gas to condense natural gas vapors in the hydrocarbon containing gas to liquid hydrocarbons. In this manner, liquid hydrocarbons and dry hydrocarbon containing gas are obtained. | 2014-09-18 |
20140260336 | METHOD OF REGULATING THE TEMPERATURE OF AN ELEMENT COOLED BY A CRYOREFRIGERATOR WITH PERIODIC OPERATION, ASSOCATED IMPLEMENTATION DEVICE AND CRYOGENIC INSTALLATION COMPRISING THIS DEVICE - The invention relates to a method of regulating the temperature of an element cooled by a cryorefrigerator with periodic operation, characterized in that it comprises the following steps: (a) measuring at least the periodic temporal evolution of the temperature T of the element, this evolution making it possible to obtain a temperature signal representative of the periodic operation of the cryorefrigerator; (b) constructing a periodic so-called equivalent thermal flux signal (Soeq), as a function of the temperature signal obtained in step (a); (c) constructing a thermal flux control signal, depending on the equivalent thermal flux signal constructed in step (b), said thermal flux control signal serving also, in return, for the construction of the equivalent thermal flux signal (ScDeq, S*oeq) during step (b); (d) injecting a thermal flux into the element, on the basis of the thermal flux signal constructed in step (c), so as to compensate for the measured periodic variations of the temperature T of the element. | 2014-09-18 |
20140260337 | Method of Producing Natural Gas from Remote and/or Isolated Offshore Reservoirs - A method of producing natural gas from at least one reservoir, the method including the steps of producing the natural gas from the at least one reservoir; liquefying a first tranche of the natural gas to produce liquefied natural gas; and compressing a second tranche of the natural gas to produce a compressed natural gas. | 2014-09-18 |
20140260338 | CRYOPUMP AND METHOD FOR REGENERATING THE CRYOPUMP - A method of regenerating a cryopump includes a first discharging process that includes alternately evacuating a cryopump housing and supplying a purge gas in a first pressure range, and a second discharging process that includes evacuating the cryopump housing to a low pressure region below the first pressure range. The second discharging process includes making a determination at least once in the low pressure range as to whether the second discharging process should be terminated, and supplying the purge gas to the cryopump housing prior to a first-time determination as to whether the second discharging process should be terminated. | 2014-09-18 |
20140260339 | CRYOPUMP SYSTEM, METHOD OF OPERATING THE SAME, AND COMPRESSOR UNIT - A cryopump system includes a cryopump, a compressor of a working gas for the cryopump, a control device configured to control an operation frequency of the compressor, a gas line connecting the cryopump and the compressor, and a gas quantity adjustment unit configured to switch a working gas quantity of the gas line between at least a first gas quantity and a second gas quantity. When the gas line has the first gas quantity, a controllable range of the operation frequency provides a first flow rate range of the working gas. When the gas line has the second gas quantity, the controllable range provides a second flow rate range of the working gas. The second flow rate range has a non-overlapping portion with the first flow rate range. | 2014-09-18 |
20140260340 | ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS - A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft. | 2014-09-18 |
20140260341 | ADAPTIVE TRANS-CRITICAL CARBON DIOXIDE COOLING SYSTEMS - A cooling system includes a first heat exchanger, an evaporator coupled to a thermal load of an aircraft. first and second cooling circuits coupled to the heat exchanger, the first and second cooling circuits selectable via a set of cooling circuit valves that are arranged to direct a refrigerant through the first circuit, the second circuit, or both the first and second circuits based on air passing through the first heat exchanger at ambient conditions of the aircraft, and a receiver configured to accumulate reserve refrigerant to provide flexibility in system operation as the cooling system operates in sub-critical, trans-critical, and super-critical modes of operation. | 2014-09-18 |
20140260342 | SYSTEM FOR REFRIGERANT CHARGE VERIFICATION - A charge-verification system for a circuit including a condenser having an inlet, an outlet, and a coil circuit tube extending between the inlet and the outlet is provided. The charge-verification system may include a first of coil temperature sensor located on the coil circuit tube a first distance from the inlet and a second of coil temperature sensor located on the coil circuit tube a second distance from the inlet. The charge-verification system may also include a controller receiving a first signal from the first temperature sensor indicative of a first temperature and a second signal from the second temperature sensor indicative of a second temperature. The controller may determine which of the first signal and the second signal is closer to an actual saturated condensing temperature of the condenser. | 2014-09-18 |
20140260343 | VARIABLE FREQUENCY DRIVE APPARATUSES, SYSTEMS, AND METHODS AND CONTROLS FOR SAME - Detection of reverse rotation or operation of a refrigerant compressor is provided. In one aspect, a detection technique includes starting the compressor and determining the compressor is rotating in a reverse direction if a dome temperature of the compressor fails to exceed a first predetermined threshold at or before expiration of a first predetermined period of time following starting, the refrigerant pressure at a refrigerant inlet of the compressor remains constant for a second predetermined period of time following starting, and/or the frequency of pressure oscillations of the refrigerant at the refrigerant inlet exceeds a second predetermined threshold. Another technique for determining the compressor is rotating in the reverse direction involves analyzing a waveform associated with motor current, motor torque, or refrigerant pressure. Further embodiments, forms, features, and aspects shall become apparent from the description and drawings. | 2014-09-18 |
20140260344 | APPLICATIONS OF LIQUID TANK AS FRESH FOOD EVAPORATOR - An appliance having a storage tank disposed on its back surface wherein the storage tank comprises a front cover and a back cover that matingly engages the front cover to form a liquid tight seal with the front cover. The storage tank further includes a phase-changing material disposed within the storage tank and a heat exchanger containing refrigerant tubing which transfers cooling from refrigerant tubing to the phase-changing solution. The storage tank, when fully charged with cooling capacity, maintains the food storage compartment at a temperature of 45° F. or less for at least 8 hours without activating a compressor. | 2014-09-18 |
20140260345 | ACTIVE INSULATION HYBRID DUAL EVAPORATOR WITH ROTATING FAN - An appliance having a fresh food storage compartment and a freezer compartment. The appliance includes a forced air coil system disposed between the fresh food storage compartment and the freezer compartment and is configured to selectively provide cooling to one or both of the at least one fresh food storage compartment and the at least one freezer compartment. The forced air coil system includes an evaporator fan configured to provide cooling to the food storage compartment, the freezer compartment, or both. | 2014-09-18 |
20140260346 | DEVICE AND METHOD FOR PRESSURIZED CRYOPRESERVATION OF A BIOLOGICAL SAMPLE - A cryopreservation device ( | 2014-09-18 |
20140260347 | ICE MAKER WITH HEATLESS ICE REMOVAL AND METHOD FOR HEATLESS REMOVAL OF ICE - An ice making module includes a conductive ice tray having a bottom surface and a barrier coating on at least a portion of the conductive ice tray. An electrical circuit in electrical communication with the conductive ice tray includes a power source and a capacitor. A switch is configured to move between a charging position, wherein the capacitor stores an electrical charge, and a pulse position, wherein the capacitor releases the electrical charge. A conductive material disposed proximate the conductive ice tray is in selective electromagnetic communication with the conductive ice tray. The electrical charge released by the capacitor generates an induced electrical current through the conductive material and a repelling electromagnetic force between the conductive ice tray and the conductive material. A water dispensing mechanism disposes water into the conductive ice tray. A cooling apparatus decrease the temperature of the water in the conductive ice tray. | 2014-09-18 |
20140260348 | METHOD TO EXTEND THE LIFE OF A TWIST ICE MAKER - An ice making apparatus for an appliance comprising an ice making tray having at least one specialty feature chosen from the group consisting of: a convex bottom surface, a ledge disposed about a perimeter of the at least one ice compartment and proximate a bottom portion of the at least one ice compartment, at least one thread extending from one corner of the at least one ice compartment to another corner of the at least one ice compartment, or any combination thereof. | 2014-09-18 |
20140260349 | METHOD AND SYSTEM FOR CONTROLLING THE INITIATION OF A FREEZE CYCLE PRE-SET TIME IN AN ICE MAKER - A novel control logic for an individual cube spray type ice machine. The duration of the freeze cycle is able to adapt to changes in inlet water temperature, changes in ambient air temperature, and the impact of warm temperatures of internal ice making parts within the ice machine due to off cycle periods. This is accomplished through a combination of starting a freeze time period only after the water temperature for the volume of water circulating over the evaporator has reached approximately 32° F., and a freeze time period value that is a function of the refrigerant temperature leaving the condenser at the time where the water reaches approximately 32° F. | 2014-09-18 |
20140260350 | REFRIGERANT RECOVERY DEVICE AND METHOD - A refrigerant recovery unit includes a refrigerant storage unit, a refrigerant circuit, a processor, and a memory. The refrigerant storage unit is configured to store a refrigerant. The refrigerant circuit is in fluid connection with refrigeration system. The refrigerant circuit is configured to recover refrigerant from the refrigeration system and recharge the refrigeration system with the refrigerant. The processor is configured to control the refrigerant recovery unit and the processor is configured to control a fan. The fan is configured to provide a flow of air to the refrigeration system. The memory is to store diagnostic software and operating software to operate the refrigerant recovery unit. | 2014-09-18 |
20140260351 | METHOD AND APPARATUS FOR IMPROVING THE CHARGE ACCURACY OF A REFRIGERANT RECOVERY UNIT - A refrigerant recovery unit with improved charging accuracy is provided. In some embodiments, the contamination of charging refrigerant can be prevented while also providing greater refrigerant flow control. In addition, methods associated therewith for servicing refrigerant containing refrigeration systems are provided. In some aspects, the methods include steps that can be used to achieve more accurate assessments of the refrigerant that is charged into the refrigeration systems during servicing. | 2014-09-18 |
20140260352 | TEMPERATURE CONTROLLED SERVICE HOSES FOR IMPROVED REFRIGERANT CHARGE ACCURACY - A method and charging apparatus for adding refrigerant to refrigerant system are provided. The disclosure includes thermally conditioning the interior of the service hoses of a refrigerant recovery unit used to charge refrigerant. The conditioning may be based on one or more temperature reading(s) and/or based on a function and may be achieved by a heater along the length of the hose, recirculating refrigerant, and/or through a parallel line of heated liquid. | 2014-09-18 |
20140260353 | Modified Hose Flush Device and Method - A refrigerant recovery system includes a refrigerant storage unit, a refrigerant charge path, a flushing path, a processor, and a memory. The refrigerant storage unit is configured to store a refrigerant. The refrigerant charge path is configured to convey the refrigerant to a refrigeration system to recharge the refrigeration system with the refrigerant. The refrigerant charge path includes a first and second service coupler and a first and second service hose. The service hoses are in fluid communication with the respective service couplers. The flushing path is configured to receive a flow of refrigerant for flushing the refrigeration charge path. The flushing path includes a first and second flushing coupler. The processor is configured to control the refrigerant recovery system to provide a flow of the refrigerant from the storage unit, through the refrigerant charge path, and to the flushing path. | 2014-09-18 |
20140260354 | Refrigerant Service Hose Check Valve Device and Method - A service hose includes a service coupler and a check valve assembly. The service coupler is configured to fluidly connect the service hose to a refrigeration system. The check valve assembly is disposed proximal to the service coupler and includes a recovery and a recharge flow path. The recovery flow path is defined by a flow of a refrigerant from the refrigeration system and flows along a first bore disposed in a body having a recovery poppet. The recharge flow path is defined by a flow of the refrigerant to the refrigeration system and flows along a second bore disposed in the body, a recharge poppet, and a biasing member. The check valve assembly is configured to provide a substantially free flow of refrigerant along the recovery flow path and also configured to provide a predetermined cracking pressure in response to the refrigerant being urged to flow along the recharge flow path. | 2014-09-18 |