Entries |
Document | Title | Date |
20080289313 | DIRECT HEATING ORGANIC RANKINE CYCLE - The present invention provides an organic Rankine cycle power system, which comprises means for superheating vaporized organic motive fluid, an organic turbine module coupled to a generator, and a first pipe through which superheated organic motive fluid is supplied to the turbine, wherein the superheating means is a set of coils through which the vaporized organic motive fluid flows and which is in direct heat exchanger relation with waste heat gases. | 11-27-2008 |
20090025362 | INFRARED SUPPRESSION SYSTEM WITH SPIRAL SEPTUM - An InfraRed Suppression System (IRSS) includes a double-walled exhaust duct and double walled septum. The double walled structure provides a flow path for secondary (non-exhaust gas) cooling air flow to slots along the surfaces exposed to exhaust gases. Exhaust gas flow past these slots draws cooling air across the duct and septum surfaces. This flow cools the surfaces close to the slots and mixes with exhaust gasses downstream to cool the exhaust plume. The septum in the shape of a helix rotating fully blocks line-of-sight to the turbine exit from the aft of the aircraft. The exhaust duct is intended to be shrouded by an aerodynamic fairing which provides an aerodynamic contour which minimizes aerodynamic impact on the aircraft. | 01-29-2009 |
20090031695 | METHODS AND APPARATUS FOR MIXING FLUID IN TURBINE ENGINES - A method of assembling a gas turbine engine includes providing at least one heat exchanger assembly including a heat exchanger and a lobed mixer extending downstream from the heat exchanger, wherein the mixer includes a plurality of lobes that each define a first chute and at least one second chute that extends between each pair of adjacent spaced-apart lobes, and coupling the at least one heat exchanger assembly within a bypass duct of the engine such that the at least one heat exchanger assembly is coupled to at least one of an outer engine casing and an inner engine casing of the turbine engine. | 02-05-2009 |
20090178383 | RECOATABLE EXHAUST LINER COOLING ARRANGEMENT - A gas turbine engine includes an exhaust liner having cold and hot sheets radially spaced from one another and interconnected by a band arranged in a cavity between the hot and cold sheets. In one example, the band is Z-shaped to permit thermal growth of the hot sheets relative to the cold sheets in the axial and radial directions. The hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space. Cooling fluid is provided to the cavity through impingement jets in the cold sheet. The slots are arranged radially between the hot sheet portions. | 07-16-2009 |
20090193780 | Power Generation System for a Marine Vessel - The present invention relates to a power generation system for a marine vessel including a gas-fired power generation unit such as a gas turbine arranged to receive unodorized natural gas that has been vaporized from LNG stored onboard the marine vessel as a source of fuel gas. Unodorized natural gas is used a source of fuel to keep air emissions to a minimum. | 08-06-2009 |
20090282803 | Emission reduction system for use with a heat recovery steam generation system - A system and method of maintaining an optimal temperature range for a catalyst section in a HRSG comprising placing a portion of the exhaust stream in a heat exchanger and superheater, diverting a second portion around the heat exchanger and superheater, combining the two portions and contacting the two portions with a catalyst section. Alternatively, a system of heat exchangers are employed to address the fluctuating exhaust temperature caused by the intermittent use of the duct burners. | 11-19-2009 |
20100000197 | IMPINGEMENT COOLING FOR TURBOFAN EXHAUST ASSEMBLY - A cooling system for a turbine exhaust assembly comprises an annular case, a flowpath ring and a splash plate. The flowpath ring is coaxially disposed within the annular case. The splash plate extends axially between the annular case and the flowpath ring. A plurality of cooling fluid apertures is formed in the annular case, in order to provide cooling fluid flow onto the splash plate. A plurality of impingement holes is formed in the splash plate, in order to provide impingement flow onto the flowpath ring. | 01-07-2010 |
20100011738 | HEAT PIPE FOR REMOVING THERMAL ENERGY FROM EXHAUST GAS - Disclosed is a turbomachine including at least one exhaust pathway along which exhaust is directed and released, and at least one exhaust processor capable of removing regulated substances from the exhaust. A plurality of heat pipes are disposed at least partially in the exhaust pathway upstream of the at least one exhaust processor. The plurality of heat pipes are capable of transferring thermal energy from the exhaust to the plurality of heat pipes thus reducing a temperature of the exhaust to increase effectiveness of the at least one exhaust processor. A method for releasing turbomachine exhaust includes urging turbomachine exhaust along at least one exhaust pathway and flowing the exhaust past a plurality of heat pipes. Thermal energy is transferred from the exhaust to the plurality of heat pipes thus reducing a temperature of the exhaust. | 01-21-2010 |
20100018180 | APPARATUS AND METHOD FOR COOLING TURBOMACHINE EXHAUST GAS - Disclosed is a turbomachine including at least one exhaust pathway along which exhaust is directed and released to ambient and at least one exhaust processor capable of removing regulated substances from the exhaust. One or more ambient air inlets are located at the at least one exhaust pathway upstream of the at least one exhaust processor. The at least one exhaust pathway is configured such that ambient air is capable of being urged into the at least one exhaust pathway through the one or more ambient air inlets by an acceleration of the exhaust along the at least one exhaust pathway. The ambient air urged into the at least one exhaust pathway reduces a temperature of the exhaust to increase effectiveness of the at least one exhaust processor. Further disclosed is a method for releasing turbomachine exhaust to ambient. | 01-28-2010 |
20100024378 | SYSTEM AND METHOD OF OPERATING A GAS TURBINE ENGINE WITH AN ALTERNATIVE WORKING FLUID - A gas turbine engine system is provided. The gas turbine engine system includes a gas turbine engine and an exhaust gas conditioning system. The gas turbine engine includes at least one combustion chamber and at least one turbine downstream from the combustion chamber. The combustion chamber is coupled in flow communication to a source of hydrocarbonaceous fuel and to a source of oxygen. The gas turbine engine is operable with a working fluid that is substantially nitrogen-free. The exhaust gas conditioning system is coupled between a discharge outlet of the gas turbine engine and an inlet of the gas turbine engine. | 02-04-2010 |
20100024379 | Gas Turbine Combustor Exhaust Gas Spray Cooling for NOx Control Using Selective Catalytic Reductions - Embodiments of the present disclosure relates to a system for reducing nitrogen oxides in a combustion exhaust gas comprising a selective catalytic reactor assembly comprising a catalyst bed for receiving a flow of the combustion exhaust gas, an exhaust gas conduit for introducing the combustion exhaust gas to the selective catalytic reactor assembly, at least one nozzle for introducing cooling water into the combustion exhaust gas before the combustion exhaust gas exits the selective catalytic reactor assembly, and at least one reductant conduit for introducing at least one reductant into the combustion exhaust gas to form a reductant/exhaust mixture before the combustion exhaust gas exits the selective catalytic reactor assembly. Embodiments of the present disclosure also relates to a method for reducing nitrogen oxides in a combustion exhaust gas by introducing a combustion exhaust gas into a selective catalytic reduction assembly comprising a catalyst bed, introducing cooling water into the combustion exhaust gas before the combustion exhaust gas exits the selective catalytic reactor assembly, reducing the temperature of the combustion exhaust gas before the combustion exhaust gas exits the selective catalytic reactor assembly, and introducing at least one reductant into the combustion exhaust gas to form a reductant/exhaust mixture before the combustion exhaust gas exits the selective catalytic reactor assembly. | 02-04-2010 |
20100031624 | FUEL HEATING VIA EXHAUST GAS EXTRACTION - A method and system for heating fuel for a gas turbine engine by using excess heat energy in the engine exhaust gas to heat the fuel and returning the cooled exhaust gas back to the engine exhaust gas stream upstream of an emissions sensor is disclosed. The method and system comprises providing a heat exchanger having an exhaust gas passage and a fuel passage, extracting high temperature exhaust gas from the engine exhaust gas stream and passing the high temperature exhaust gas through the exhaust gas passage. Fuel is passed through the fuel passage where excess heat energy in the high temperature exhaust gas is used to heat the fuel. The temperature of the heated fuel is controlled by controlling the flow of the high temperature exhaust gas through the exhaust gas passage. | 02-11-2010 |
20100031625 | SYSTEMS AND METHOD FOR CONTROLLING STACK TEMPERATURE - Systems and a method for controlling a temperature of an exhaust gas stack are provided. The system includes a first heat exchanger positioned upstream in exhaust gas flow communication to an exhaust gas inlet to the stack, a second heat exchanger positioned upstream in exhaust gas flow communication to the first heat exchanger, and a water side conduit configured to direct a flow of relatively hot water from the second heat exchanger to the first heat exchanger such that a temperature of a flow of exhaust gas flowing through the first exchanger is maintained within a predetermined range. | 02-11-2010 |
20100043386 | METHODS AND APPARATUS FOR MIXING FLUID IN TURBINE ENGINES - A method of assembling a gas turbine engine is provided. The method includes providing at least one heat exchanger assembly including a heat exchanger and a mixer extending downstream from the heat exchanger. The mixer includes a plurality of windows formed therein. The method also includes coupling the at least one heat exchanger assembly within a bypass duct of the engine such that the at least one heat exchanger assembly is coupled to at least one of an outer engine casing and an inner engine casing of the turbine engine. | 02-25-2010 |
20100064655 | SYSTEM AND METHOD FOR MANAGING TURBINE EXHAUST GAS TEMPERATURE - A system for thermal management of exhaust gas includes: a nozzle configured to be disposed in fluid communication with an exhaust of a turbomachine; a mixing conduit in fluid communication with the nozzle; at least one secondary inlet disposed around a periphery of the nozzle and extending between an exterior of the mixing conduit and an interior of the mixing conduit; a variable nozzle mechanism configured to be movable between i) a first position in which the mechanism is configured to close the at least one secondary inlet and ii) a second position in which the mechanism is configured to open the at least one secondary inlet and adjust a selected diameter of the nozzle; and an actuator configured to move the variable nozzle mechanism between the first position and the second position. | 03-18-2010 |
20100132330 | METHOD AND APPARATUS FOR SUPPRESSING AEROENGINE CONTRAILS - A method of operating an aircraft, and the aircraft itself, comprising a gas turbine engine that exhausts a plume of gases in use, the aircraft is characterised by comprising an electromagnetic radiation generator and a waveguide to direct electromagnetic radiation at the exhaust plume to avoid the formation of contrails. | 06-03-2010 |
20100146926 | SYSTEM FOR RECOVERING WATER FROM FLUE GAS - A power plant may include a combustion apparatus ( | 06-17-2010 |
20100199626 | TURBINE ENGINE EXHAUST GAS TUBE MIXER - An exhaust mixer for an engine is provided having multiple flow tubes arranged in an annular array. A cooling space is formed to allow the passage of cooling air between the flow tubes and within the annular array. In one form the exhaust mixer can be constructed from multiple, individual exhaust flow tubes. The flow tubes can be constructed to engage neighboring flow tubes to create the annular array of exhaust flow tubes. The flow tubes can be interchangeable with other flow tubes. | 08-12-2010 |
20100205927 | APPARATUS FOR A NITROGEN PURGE SYSTEM - A method for reducing the emissions from combustion gases produced during a combustion process includes injecting a hydrocarbon-based reducing agent into the combustion gases to form a combustion gas mixture. The combustion gas mixture including oxides of nitrogen, NO | 08-19-2010 |
20100269480 | Gas turbine exhaust diffuser - A gas turbine including an exhaust diffuser with a flow splitter located between the inner wall and outer wall defining the exhaust gas flow path. In one aspect the flow splitter being moveable independent of the walls defining the exhaust gas flow path to allow for differing thermal movement between the components. In one form a structural member extends from a wall and is coupled to the flow splitter. The wall can have an opening for the through which the structural member is allowed to pass. In some forms a plurality of structural members can be coupled to the flow splitter. In other forms the flow splitter can be independently movable relative to the wall. | 10-28-2010 |
20100300061 | Selective Catalytic Reduction System and Process for Treating NOx Emissions Using a Palladium and Rhodium or Ruthenium Catalyst - A process for the catalytic reduction of nitrogen oxides (NOx) in a gas stream ( | 12-02-2010 |
20110000181 | NOISE REDUCING DEVICE AND JET PROPULSION SYSTEM - A noise reducing device in a jet engine that has a cylindrical casing, a cylindrical partition wall that is inserted in the casing while protruding partially from a trailing edge of the casing, and a compressor that compresses air that is taken into the cylindrical partition wall, with the inside of the cylindrical partition wall serving as a duct in which a core stream of high-speed air flows, and the space between the cylindrical partition wall and the casing serving as a duct in which a bypass stream of low-speed air flows, and being connected with a wing of an airplane by a pylon that has a projection portion that extends beyond the casing to the downstream of the core stream and the bypass stream, the noise reducing device includes a nozzle, disposed at the pylon on the downstream of the core stream, that injects a fluid toward a noise generation source that is produced from the mutual approach of an ambient air stream that is produced outside of the bypass stream and the core stream. | 01-06-2011 |
20110011052 | GAS TURBINE EXHAUST GAS COOLING SYSTEM - A gas turbine exhaust gas cooling system includes a conduit for a primary gas turbine exhaust gas extending from the primary gas turbine to an inlet of a desired industrial process apparatus, a work producing thermodynamic cycle in which a working fluid is heated and expanded, and at least one heat exchanger by which heat is sufficiently transferred from the primary gas turbine exhaust gas to the working fluid to produce a low temperature heating medium downstream of the heat exchanger at a predetermined temperature and energy level which are sufficient for effecting a desired industrial process. | 01-20-2011 |
20110016844 | DEVICE FOR REDUCING TURBOPROP INFRARED EMISSIONS - According to the invention, fresh air (E) at the turboprop outlet is captured and mixed with the warm airflow (F) created by said turboprop to lower the temperature. | 01-27-2011 |
20110030331 | Ammonia Injection System - In one embodiment, a system includes an emissions reduction system including a compressor in fluid communication with a catalyst mixing tank. The compressor is configured to output an air flow configured to deliver catalyst from the catalyst mixing tank to a catalyst injection grid. A temperature of the air flow is increased by the compressor. | 02-10-2011 |
20110056179 | TURBINE EXHAUST DIFFUSER WITH REGION OF REDUCED FLOW AREA AND OUTER BOUNDARY GAS FLOW - An exhaust diffuser system and method for a turbine engine. The outer boundary may include a region in which the outer boundary extends radially inwardly toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. At least one gas jet is provided including a jet exit located on the outer boundary. The jet exit may discharge a flow of gas downstream substantially parallel to an inner surface of the outer boundary to direct a portion of the exhaust flow in the diffuser toward the outer boundary to effect a radially outward flow of at least a portion of the exhaust gas flow toward the outer boundary to balance an aerodynamic load between the outer and inner boundaries. | 03-10-2011 |
20110162339 | FLOW DISTRIBUTION OF GAS TURBINE EXHAUST USING WALLS SHAPED TO FACILITATE IMPROVED GAS FLOW - A gas turbine transition into an emission reduction catalyst is improved by adding properly curved surfaces so as to induce the Coanda effect. Such a surface allows for a reduction in pressure drop, shorter duct lengths, and elimination of some or all of traditionally used flow re-distribution devices. | 07-07-2011 |
20110258980 | PROCESS FOR CO-GENERATION OF MECHANICAL-ELECTRICAL ENERGY AND HEAT - This invention relates to a process for the production of electrical or mechanical energy and heat from a liquid fuel that comprises:
| 10-27-2011 |
20110302902 | INTEGRATED ENGINE EXHAUST AND HEAT PROCESS FLEXIBLE AND LOW EMISSIONS COMBINED HEAT AND POWER PROCESS AND SYSTEM - The invention provides systems and methods for electric power production and integrated combustion and emissions control. The invention may include an engine capable of receiving air and fuel, and producing power and an engine exhaust gas. The invention may also include a first reaction zone receiving the engine exhaust gas from the engine configured to combust fuel and air having an equivalence ratio of more than one, thereby generating a first product. The combustion may reduce nitrogen containing species. The invention may also include a second reaction zone receiving the engine exhaust gas from the engine configured to combust fuel and air having an equivalence ratio of less than one, thereby generating a second product. The combustion may reduce or minimize NOx. The invention may also include a mixing zone configured to receive the first product and second product, and mix and react the first and second products, thereby generating an exhaust with reduced NOx levels. This may occur with sufficient residence time and temperature to complete combustion and promote nitrogenous species reduction reactions. For inventions with multiple zones, fuel or air or exhaust gas may be adjusted, diverted or turned off as load is reduced to maintain flame stability for all zones that remaining operational. For inventions with engine exhaust that provides less oxidant than the burner requires, an air eductor means may be arranged between the engine and the burner that entrains needed additional oxidant and simultaneously recovers the flow energy in the turbine exhaust. | 12-15-2011 |
20110308228 | Fin and Tube Heat Exchanger - The present application provides a fin and tube heat exchanger. The fin and tube heat exchanger may include a number of tubes with a number of fins positioned on each of the tubes. The tubes may include a first set of tubes and a second set of tubes with the first set of tubes including an offset position as compared to the second set of tubes. | 12-22-2011 |
20120102910 | High Flow Eductor - An exhaust eductor for a gas turbine engine comprises: an engine exhaust chamber with an exhaust chamber inlet that receives engine exhaust from the gas turbine engine and an exhaust chamber outlet that discharges the engine exhaust to establish an exhaust gas flow through the engine exhaust chamber; an air chamber with an air inlet that receives ambient air external to the gas turbine engine; and a mixing baffle that couples the air chamber to the engine exhaust chamber, comprising a first side adjacent the air chamber, a second side adjacent the exhaust chamber, multiple apertures through the mixing baffle that extend from the first side to the second side of the mixing baffle, each aperture having a corresponding canopy that extends from an upstream end of the aperture along the second side of the mixing baffle into the exhaust gas flow for at least a portion of the length of the aperture, to establish an air flow from the air inlet of the air chamber into the exhaust gas flow. | 05-03-2012 |
20120131897 | Carbon Dioxide Compression Systems - The present application provides a gas compression system for use with a gas stream. The gas compression system may include a number of compressors for compressing the gas stream, one or more ejectors for further compressing the gas stream, a condenser positioned downstream of the ejectors, and a waste heat source. A return portion of the gas stream may be in communication with the ejectors via the waste heat source. | 05-31-2012 |
20120198810 | STRUT AIRFOIL DESIGN FOR LOW SOLIDITY EXHAUST GAS DIFFUSER - This disclosure relates to a strut airfoil for use in an exhaust diffuser. The strut airfoil described herein generally is asymmetric. The strut airfoil has a curved leading edge, a curved tail edge, and two surfaces connecting the leading edge and tail edge. This disclosure also relates to gas turbines that contain an exhaust diffuser with struts that are covered with a strut airfoil. | 08-09-2012 |
20130019583 | DIFFUSER WITH BACKWARD FACING STEP HAVING VARYING STEP HEIGHT - A diffuser ( | 01-24-2013 |
20130125524 | EMISSIONS CONTROL SYSTEMS AND METHODS - Methods and systems are provided related to an emissions control system. The emissions control system has an exhaust after-treatment system defining a plurality of distinct exhaust flow passages through which at least a portion of an exhaust stream can flow, e.g., the exhaust stream is produced by an engine. The emissions control system also includes a controller for controlling injection of reductant into the exhaust stream flowing through each of the flow passages. In one example, the emissions control system is configured for use in a vehicle, such as a locomotive or other rail vehicle. | 05-23-2013 |
20130205743 | SELECTIVE CATALYTIC REDUCTION SYSTEM AND PROCESS FOR CONTROL OF NOx EMISSIONS IN A SULFUR-CONTAINING GAS STREAM - An exhaust gas treatment process, apparatus, and system for reducing the concentration of NOx, CO and hydrocarbons in a gas stream, such as an exhaust stream ( | 08-15-2013 |
20130213000 | AUTOMOBILE EXHAUST GAS CATALYTIC CONVERTER - An automobile exhaust gas catalytic converter includes a first catalyst layer; a second catalyst layer located on a downstream side as compared to the first catalyst layer; and a base material on which the first catalyst layer and the second catalyst layer are respectively located. In the exhaust gas catalytic converter, the proportion (L | 08-22-2013 |
20130276423 | GAS TURBINE - A compressor compresses air to produce compressed air. A mixture of fuel and the compressed air is combusted in a combustor to produce combustion gas. The combustion gas is supplied to a turbine to obtain rotational power. High-temperature gas accumulated in a space partitioned by an exhaust-side bearing portion that rotatably supports a turbine shaft and an exhaust diffuser is discharged through an exhaust gas passage. The high-temperature gas is sucked into the exhaust gas passage by exhaust gas flowing in the exhaust diffuser. | 10-24-2013 |
20130291513 | TURBOMACHINE COMPONENT HAVING AN INTERNAL CAVITY REACTIVITY NEUTRALIZER AND METHOD OF FORMING THE SAME - A turbomachine component includes a body having an exterior surface and an interior surface, an internal cavity defined by the interior surface, and a reactivity neutralizing member arranged within the internal cavity. The reactivity neutralizing member is configured and disposed to neutralize turbomachine combustion products on the interior surface of the body. | 11-07-2013 |
20140041357 | EXHAUST DIFFUSER INCLUDING FLOW MIXING RAMP FOR A GAS TURBINE ENGINE - A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs. | 02-13-2014 |
20140047813 | EXHAUST COLLECTOR WITH RADIAL AND CIRCUMFERENTIAL FLOW BREAKS - An exhaust collector having a radial inlet configured to receive exhaust gas in a radial direction, an outlet configured to deliver exhaust gas in and outlet direction, and an enclosure configured to collect the received exhaust gas into at least two circumferential counter flows, and route the collected exhaust gas to the outlet, wherein the enclosure includes a collected flow barrier configured to divide the collected exhaust gas from the exhaust gas received at the radial inlet, and a collected flow circumferential divider configured to form a physical barrier between at least a portion of the at least two circumferential counter flows. | 02-20-2014 |
20140090353 | Systems and Methods for Determining a Target Exhaust Temperature for a Gas Turbine - Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine. The method can include determining a target exhaust temperature based at least in part on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based at least in part on steam humidity; and changing the target exhaust temperature based at least in part on the temperature adjustment. | 04-03-2014 |
20140090354 | TURBINE EXHAUST PLUME MITIGATION SYSTEM - Various embodiments include an exhaust plume mitigation system for a turbine and systems incorporating the exhaust plume mitigation system. In some embodiments, the exhaust plume mitigation system includes: a first conduit fluidly connecting a compressor to an exhaust chamber of the turbine; a first control valve operably connected with the first conduit for regulating flow of compressor air through the first conduit; and a fluid inductor including: a first inlet fluidly connected with the first conduit; a second inlet fluidly connected with ambient; and an outlet fluidly connected with the exhaust chamber. | 04-03-2014 |
20140096500 | EXHAUST DIFFUSER - An exhaust diffuser includes an outer shroud and an inner shroud radially separated from the outer shroud so as to define a fluid passage between the outer shroud and the inner shroud. A strut extends between the outer shroud and the inner shroud. The strut generally includes an outer surface, a leading edge, a trailing edge, a first side and a second side. At least one turbulator may be positioned along a radial span of the strut. The at least one turbulator extends generally outwardly from the strut outer surface. The turbulator extends across the leading edge of the strut from the first side to the second side of the strut. | 04-10-2014 |
20140096501 | UPTURNED EXHAUST SYSTEM FOR ROTARY WING AIRCRAFT - An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a manifold; an opening in the manifold, the opening configured to face upwards and away from the rotary wing aircraft; and a chimney including a wall positioned about the opening, the chimney configured to eject an emission of intermixed secondary air and engine exhaust upwards and away from the rotary wing aircraft. | 04-10-2014 |
20140137533 | EXHAUST GAS DIFFUSER FOR A GAS TURBINE - An exhaust gas diffuser for a gas turbine generally includes an inner wall that extends along an axial centerline of the exhaust gas diffuser. An outer wall is coaxially aligned with the inner wall. The outer wall is radially separated from the inner wall so as to define a flow passage therebetween. An airfoil shaped strut is disposed in the flow passage. The strut extends between the inner and the outer walls. The strut includes a leading edge and a trailing edge positioned relative to a direction of flow through the flow passage. The leading edge and the trailing edge are tapered from the inner wall to the outer wall in the direction of flow through the passage. | 05-22-2014 |
20140150399 | DIVERTER DAMPER - The invention relates to a diverter damper for controlling a gas flow in a gas duct of large cross section, said diverter damper comprising:—a housing having an inlet and two outlets,—a pivotable flap which in a first extreme position closes a first outlet and in a second extreme position closes a second outlet,—a drive shaft connected to the pivotable flap, wherein the drive shaft extends at least partly between two opposite housing walls and through at least one of the two opposite housing walls,—at least one actuator mechanism that is located outside the housing near or against the at least one housing wall through which the drive shaft extends, wherein said actuator mechanism comprises at least one cylinder piston unit connected to said drive shaft for pivoting the flap into one of the extreme positions or into a position between the extreme positions. | 06-05-2014 |
20140174052 | EXHAUST DIFFUSER AND METHOD FOR MANUFACTURING AN EXHAUST DIFFUSER - An exhaust diffuser and method for manufacturing an exhaust diffuser is provided. An exhaust diffuser for a torque-generating turbine, in particular a torque-generating gas turbine is provided, the exhaust diffuser having an inner member, and the inner member having an outer surface. The outer member having an inner surface, and the inner member and the outer member forming an annular channel at least a first supporting strut connecting the inner member and the outer member, the supporting strut extending essentially radially from the inner surface to the outer surface, the supporting strut having a middle section, the middle section having a first airfoil and an outer section having a second airfoil, and the second airfoil having a higher angle of incidence than the first airfoil. Furthermore, it is described a method for manufacturing an exhaust diffuser. | 06-26-2014 |
20140215999 | AFT EXHAUST SYSTEM FOR ROTARY WING AIRCRAFT - An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a duct assembly having an inlet portion and an outlet portion; the inlet portion configured to receive exhaust from an engine of the aircraft; and the outlet portion coupled to the inlet portion, the outlet portion having an outlet duct with an outlet opening, the outlet duct configured expel an emission containing engine exhaust proximate to a tail fairing of the rotary wing aircraft. | 08-07-2014 |
20140230400 | HEAT RETENTION AND DISTRIBUTION SYSTEM FOR GAS TURBINE ENGINES - A gas turbine engine including a compressor section, a combustor section, and a turbine section operating to produce a power output during a first mode of operation. A heat retention and distribution system is provided to the engine wherein the heat retention system operates in a second mode of operation, following a shutdown of the engine, to maintain an elevated temperature in components of each of the compressor section, the combustor section and the turbine section in order to effect (1) a reduction in an effective cyclic life consumption of the components and extend a maintenance interval associated with the effective cyclic life consumption, and (2) clearances by maintaining a higher vane carrier temperature with time during a non-power producing mode and more uniform temperature of most stationary components in the circumferential orientation. | 08-21-2014 |
20140250857 | LOW-CONCENTRATION METHANE GAS OXIDATION SYSTEM USING EXHAUST HEAT FROM GAS TURBINE ENGINE - A low-concentration methane gas oxidation system is provided which effectively uses exhaust heat from a gas turbine engine and is able to avoid burnout of a catalyst etc. to enable stable operation even when a methane concentration in a low-concentration methane gas which is a treatment target is rapidly increased. In a low-concentration methane gas oxidation system which oxidizes a low-concentration methane gas by using exhaust heat from a gas turbine engine, a supply source of the low-concentration methane gas which is an oxidation treatment target, a catalyst layer configured to oxidize the low-concentration methane gas by catalytic combustion, and an intake damper connected to a supply passage through which the low-concentration methane gas is supplied from the supply source to the catalyst layer and configured to introduce an air from an outside into the supply passage, are provided. | 09-11-2014 |
20140298771 | GAS TURBINE EXHAUST DIFFUSER - A gas turbine exhaust diffuser includes a frustoconical portion that defines an interior surface and an axial centerline. In particular embodiments, the interior surface may have a slope greater than 6 degrees, 10 degrees, or 20 degrees with respect to the axial centerline to define an axial cross-sectional area of at least 200 square feet, 240 square feet, or 260 square feet. In other particular embodiments, the interior surface may have an axial length of less than 25 feet or less than 10 feet. A helical turbulator on the interior surface of the frustoconical portion may reduce flow separation between exhaust gases and the interior surface to enhance recovery of potential energy from the exhaust gases. | 10-09-2014 |
20140331637 | TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH AN ELONGATED EJECTOR - A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing. The upper side region may be positioned above a horizontally extending centerline of the casing. Fluids may be exhausted from one or more exhaust slots in the casing temperature control housing to isolate the upper side region of the casing from buoyancy effects of hot gases within the casing after shutdown of the gas turbine engine. | 11-13-2014 |
20140331638 | METHOD FOR PRODUCING A CATALYST FLOW ELEMENT AND CATALYST FLOW ELEMENT - To provide a method for producing a catalyst flow element ( | 11-13-2014 |
20140373504 | GAS TURBINE HAVING AN EXHAUST GAS DIFFUSER AND SUPPORTING FINS - A gas turbine having an exhaust gas diffuser connected to a turbine unit is provided, wherein the gas diffuser channel of the gas diffuser is delimited on the outside by a channel wall and has a plurality of hollow supporting fins extending inward for fastening a radial bearing of the gas turbine, wherein at least one blow-off line for blow-off air having at least one pipeline ends at the outlet side on the exhaust gas diffuser and the end of the exhaust gas diffuser on the inlet side is connected to a compressor of the gas turbine. In order to at least partially compensate for incorrect incident flow of the supporting fins, more particularly in partial load operation, the supporting fins have a hub on the inner end thereof, the axial end of said hub having additional openings for blowing out the blow-off air in the diffuser channel. | 12-25-2014 |
20150059312 | EXHAUST STACK HAVING A CO-AXIAL SILENCER - An exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis. A co-axial silencer is arranged in one of the inlet section and outlet section. The co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack. | 03-05-2015 |
20150075131 | EXHAUST COLLECTOR WITH CURVED SIDE PANEL - An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel. The side panel includes a circumferential portion, a first contoured portion, and a second contoured portion. The circumferential portion extends about the exhaust collector axis with a constant radius. The first contoured portion and the second contoured portion are each between the circumferential portion and the exhaust outlet and include a plurality of curved sections with alternating concavity. Each of the plurality of curved sections extends from the front panel to the rear panel. | 03-19-2015 |
20150128557 | MICROSCALE DISTRIBUTED ENERGY COGENERATION METHOD AND SYSTEM - A microscale energy cogeneration system includes at least a micro/nano-turbine set for converting fuel into mechanical energy, and a generator for converting mechanical energy produced by said micro/nano-turbine into electrical energy in the range of 1 to 5 kWh. The system further includes an exhaust passage downstream from said micro/nano-turbine delivering high temperature exhaust air from said micro/nano-turbine. At least one heat exchanger receives high temperature exhaust air from said exhaust passage for heat transfer. Said heat exchanger may be used to heat water and/or air of a house. A water heating system may be coupled to the heat exchanger for convening tap water into hot water and/or cool heating air into hot air. The portable micro/nano-turbine set may be scaled up by interconnecting several units at the same time and/or interconnecting different units of different users for balancing out the energy demand of those users. | 05-14-2015 |
20160131045 | EMISSIONS CONTROL SYSTEM FOR A GAS TURBINE ENGINE - An emissions control system ( | 05-12-2016 |
20160169071 | COMBINED HEAT AND POWER SYSTEM | 06-16-2016 |
20160186626 | ENGINE COMPONENT AND METHODS FOR AN ENGINE COMPONENT - An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a multi-faceted diffusing section configured to improve the adhesion of a coating on the substrate. | 06-30-2016 |
20160376955 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow system for a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; an airflow generation system for attachment to a rotatable shaft of the gas turbine system, the airflow generation system and the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system and the compressor component to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream. | 12-29-2016 |
20160376956 | POWER GENERATION SYSTEM EXHAUST COOLING - A system for reducing a temperature of an exhaust gas stream of a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; an airflow generation system for attachment to a rotatable shaft of the gas turbine system, the airflow generation system and the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system and the compressor component to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and a fluid injection system for injecting an atomized fluid into the mixing area to reduce a temperature of the exhaust gas stream. | 12-29-2016 |
20160376957 | POWER GENERATION SYSTEM EXHAUST COOLING - A power generation system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; an airflow generation system coupled to an expander shaft downstream of the gas turbine system for drawing in a flow of ambient air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system;
| 12-29-2016 |
20160376958 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow control system for a combined cycle power generation system according to an embodiment includes: a compressor component of a gas turbine system for generating an excess flow of air; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; and an air extraction system for extracting at least a portion of the excess flow of air generated by the compressor component of the gas turbine system to provide bypass air, and for diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; wherein the reduced temperature exhaust gas stream is provided to a heat recovery steam generator. | 12-29-2016 |
20160376959 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow control system for a combined cycle turbomachine system according to an embodiment includes: an airflow generation system for attachment to a rotatable shaft of a gas turbine system, the airflow generation system drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for extracting a first portion of the excess flow of air to provide bypass air, and for diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; diverting a second portion of the excess flow of air into the compressor component; and in response to an increase in a temperature of the air, increasing the second portion of the excess flow of air diverted into the compressor component. | 12-29-2016 |
20160376961 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow control system for a gas turbine system according to an embodiment includes: an airflow generation system for attachment to a rotatable expander shaft of a gas turbine system, downstream of the gas turbine system, for drawing in a flow of ambient air through an air intake section into a mixing area; and an eductor nozzle for attachment to a downstream end of the turbine component for receiving an exhaust gas stream produced by the gas turbine system and for drawing in a flow of ambient air through the air intake section into the mixing area, the exhaust gas stream passing through the eductor nozzle into the mixing area; wherein, in the mixing area, the exhaust gas stream mixes with the flow of ambient air drawn in by the airflow generation system and the flow of ambient air drawn in by the eductor nozzle to reduce a temperature of the exhaust gas stream. | 12-29-2016 |
20160376967 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow control system for a gas turbine system according to an embodiment includes: an airflow generation system for attachment to a rotatable shaft of a gas turbine system for drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for extracting at least a portion of the excess flow of air generated by the airflow generation system to provide bypass air; an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage and around the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream. | 12-29-2016 |
20160376991 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow control system for a gas turbine according to an embodiment includes: an airflow generation system for attachment to a rotatable shaft of a gas turbine system, the airflow generation system drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream of the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream. | 12-29-2016 |
20160376992 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow control system for a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system for generating an excess flow of air; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for extracting at least a portion of the excess flow of air generated by the compressor component of the gas turbine system to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream. | 12-29-2016 |
20160376994 | POWER GENERATION SYSTEM EXHAUST COOLING - An airflow control system for a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for extracting a supply of bypass air from an excess flow of air generated by the compressor component of the gas turbine system; an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage and around the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream. | 12-29-2016 |
20160377028 | CATALYTIC N2O PILOT IGNITION SYSTEM FOR UPPER STAGE SCRAMJETS - There is disclosed a system including a catalytic heat exchanger reactor configured to carry out exothermic decomposition of stable chemical species possessing positive heats of formation. In an embodiment, the reactor is configured to enhance decomposition reaction rates by contacting gas entering with a hot surface. The catalytic heat exchanger is configured to receive N | 12-29-2016 |