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WO/2007/073185A1 |
Rotary combustion device (1) with rotary combustion chamber (4). Specific measures are taken to provide ignition of a combustible mixture. It is proposed that a hollow tube be provided coaxially with the axis of rotation (6), so that a s...
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WO/2007/069308A1 |
A micro gas turbine system the generating efficiency and the generation output of which are increased by means of water spray and in which an effective water spray control is made with simplified control. In the micro gas turbine system ...
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WO/2007/065930A1 |
The improvement, in a process for the catalytic hydrogenation of atmospheric carbon dioxide carried out in a hydrogenation reactor (1) generating liquid and/or gaseous hydrocarbons, consists in recovering said liquid and/or gaseous hydro...
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WO/2007/060158A1 |
The invention relates to a housing (30) for a cylindrical combustion chamber that extends perpendicularly on a gas turbine. Said housing comprises a plurality of wall and ceiling panels (25, 26) which form a hood and surround the cylindr...
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WO/2007/057754A2 |
A gas turbine system (1), employing steel plant gas as fuel, has at least a combustion air compressor (17); at least a steel plant gas compressor (6); a combustion chamber (14) which receives the compressed combustion air and compressed ...
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WO/2007/053323A2 |
An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between th...
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WO/2007/047270A1 |
A method of reducing a modified Wobbe index of a fuel stream (80) fed to diffusion combustors (78) of a gas turbine (62) that is used in connection with an IGCC installation in which a nitrogen stream (54) is fed into the head ends of th...
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WO/2007/036964A1 |
Method for starting a gas turbine equipped with a burner (1), which has an axial swirler (16) for generating turbulence in a flow of comburent air, a secondary supply line of fuel gas (36), a main supply line of fuel gas (6) arranged con...
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WO/2007/032738A1 |
The present invention discloses a method and system for augmenting shaft output of stationary gas turbines that can be used in multiple modes of operation. The system comprises a washing unit (25, 27, 28) adapted to inject a spray (26) o...
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WO/2007/031658A1 |
The invention concerns a method for reducing CO2 rate present in fumes released by a power generator burning a mixture of oxidant and fuel containing hydrocarbons, which consists in expanding the combustion fumes, compressing a gas mixtu...
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WO/2007/028689A1 |
An apparatus for mixing gas streams includes a duct (20) for carrying the first gas stream in a certain direction (22); at least one conduit (32) for carrying the second gas stream so that it interacts with the first gas stream, and a nu...
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WO/2007/025822A1 |
The invention relates to an apparatus for modifying the content of a gaseous fuel comprising: a supply of the gaseous fuel (2); a supply of an oxidant (3); and a combustion device (1, 9, 10) for utilising the oxidant to partially combust...
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WO/2007/023449A2 |
An engine (10) consists, in combination, of a gas turbine and a ducted fan with a combustion chamber (16) or the gas turbine being positioned radially outwardly of the flow passage of the ducted fan. The gas turbine includes a compressor...
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WO/2007/023326A1 |
A cogeneration plant has an electric generator (1) that receives, from a shaft (2) of a reduction gear (3), mechanical energy transmitted by a power turbine (5) to a shaft. (4) through an inlet reduction gear (3) . The power turbine (5) ...
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WO/2007/024674A2 |
A turbine engine (10) particularly suited f or VTOL aircraf t is disclosed. The Core of the turbine engine can include two spools - a low pressure (LP) spool (14) and a high pressure (HP) spool (12) - where the LP spool is independently ...
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WO/2007/017498A1 |
The invention relates to a method for the aerodynamic design of a compressor of a turbine engine, in particular, a compressor of a gas turbine, wherein a water flow may be continuously mixed with the working fluid flow of the compressor ...
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WO/2007/017490A1 |
The invention relates to a method for operating a gas turbine (11) in a combined-cycle power plant (40), in which method air is sucked in and compressed by the gas turbine (11), and the compressed air is fed to a combustion chamber (18, ...
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WO/2007/017487A1 |
The invention relates to a method for operating a gas turbine (11) in a combined-cycle power plant (40), in which method air is sucked in and compressed by the gas turbine (11), which air is fed to a combustion chamber (18, 19) for the c...
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WO/2007/019336A2 |
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 exhau...
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WO/2007/017406A1 |
The invention relates to a method for operating a gas turbine (11) in a combined power plant (40) as well as a gas turbine for carrying out said method. According to the inventive method, air is sucked in and compressed by the gas turbin...
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WO/2007/015916A2 |
A fan-turbine rotor assembly (24) includes a diffuser (114) mountable to the outer periphery of a multitude of hollow fan blade sections (72) to provide structural support to the outer tips of the fan blade sections and to turn and diffu...
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WO/2007/000390A1 |
The invention relates to a method for increasing aerodynamic stability of a flow of working fluid of a compressor of a turbo machine, in particular, a compressor of a gas turbine which is used to produce a current, in particular, in rela...
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WO/2007/000157A2 |
The invention relates to a system and a method for generating energy by recycling waste using combined heating and power stations. The aim of the invention is to ensure an inexpensive, sustainable supply of electric and thermal energy fo...
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WO/2007/002422A1 |
Systems and methods of integrating plasma waste processing are described. An integrated energy generation system provided with a fossil fuel power plant system having a combustion chamber and a plasma waste processing system having an ou...
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WO/2006/137723A1 |
The invention relates to a radial flow gas turbine consisting of: a rotor comprising an axial compressor that is combined with a centrifugal compressor and a radial flow turbine zone, and a stator which supports the rotor and which conta...
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WO/2006/138223A2 |
A gas storage assembly that has an enclosure within which are disposed at least about 100 inorganic tubules are present for each cubic micron of volume of the enclosure. The assembly has a storage capacity of at least 20 grams of hydroge...
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WO/2006/129398A1 |
A gasification equipment provided with a gasification furnace (23) for fuel gas production is provided. A hybrid power generation equipment (25), which generates electric power by rotating a gas turbine using a steam turbine in combinati...
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WO/2006/123995A1 |
Method for efficient energy transformation by means of a gaseous medium comprising steam, said steam being produced from a first fluid medium, energy for heating the first fluid medium being provided by burning a fuel, comprising the ste...
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WO/2006/121503A1 |
A gasification power plant (10) includes a compressor (32) producing a compressed air flow (36), an air separation unit (22) producing a nitrogen flow (44), a gasifier (14) producing a primary fuel flow (28) and a secondary fuel source (...
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WO/2006/121335A1 |
A method for generating steam under pressure, primarily for injection into the combustion chamber of a gas turbine, comprises a system having a low pressure generator (1) and a high pressure generator (2) receiving heat from the exhaust ...
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WO/2006/121506A1 |
A fan-turbine rotor hub (64) includes an outer periphery scalloped by a multitude of elongated openings (114). Each elongated opening defines an inducer receipt section to receive an inducer section (66) and a hollow fan blade section (7...
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WO/2006/117073A1 |
The invention relates to an internal combustion engine exhaust-gas turbocharger comprising the turbine wheel of a turbine which is totally connected to the compressor impeller of a compressor by means of a shaft, wherein the compressor h...
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WO/2006/112807A2 |
In order to start a turbine engine (10), high-pressure fluid is directed onto a turbine (34a) to cause rotation of the turbine and thereby start the turbine engine. In a disclosed embodiment, the high-pressure fluid is provided through a...
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WO/2006/110125A2 |
Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an exam...
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WO/2006/110124A2 |
A tip turbine engine (10) includes a combustor (30) radially outward of a fan. In order to reduce the heat transfer from the combustor and the high-energy gas stream generated by the combustor, a cold air ejector (38) radially outward of...
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WO/2006/105739A1 |
A refrigeration system and refrigeration method thereof utilizing the principle of thermodynamics comprises a compressor, an air cooler connected to the compressor, an expander having a first end connected to the air cooler, a second end...
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WO/2006/102174A2 |
An apparatus for generating a high pressure fluid from a low pressure gas source, includes a low pressure gas source for supplying a low pressure gas, a vessel for receiving the low pressure gas, cooling means for cooling the low pressur...
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WO/2006/100342A1 |
Invention relates to a method of operating a gas engine plant (1) comprising a combustion engine (3) adapted to be combust gaseous fuel and a fuel feeding system of the combustion engine with a source of fuel (2), the method being charac...
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WO/2006/083320A2 |
The present invention provides an ultra micro gas turbine engine which includes a wave rotor. In various embidiments, the ultra micro gas turbine engine of the present invention includes a rotating disk which has a compressor, a wave rot...
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WO/2006/077642A1 |
A method of correcting the balance of a gas turbine formed so that a balance between the generator side shaft end of a rotor and the shaft end of the gas turbine can be corrected within the range of service rotational speed. In the metho...
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WO/2006/061929A1 |
A gas turbine engine having a foreign matter removal passage enabling the effective removal of foreign matters in a combustion air while adopting an extremely simple structure, wherein an intake passage (21) comprises an inlet part (29),...
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WO/2006/062497A1 |
A tip turbine engine assembly (8) includes a fan (32) rotatable in a fan plane (22) about an engine centerline (112). The fan (32) includes a fan blade (34) that defines a core airflow passage therethrough. An engine case (10) surrounds ...
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WO/2006/060883A1 |
The present invention is related to a process and an installation for the production of electric power or the cogeneration of electric and thermal power, wherein a hydrocarbon fuel is enriched through an endothermic reforming reaction on...
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WO/2006/060001A1 |
A fan-turbine rotor assembly (24) for a tip turbine engine (10) includes a fan hub (64) with an outer periphery (112) scalloped by a multitude of elongated openings (114) which extend into a fan hub web (115). Each elongated opening defi...
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WO/2006/059989A1 |
A tip turbine engine assembly according to the present invention includes a load bearing engine support structure (12). The engine support structure (12) includes an engine support plane (P) that is substantially perpendicular to an engi...
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WO/2006/059968A1 |
A tip turbine engine (10) provides an axial compressor rotor (46) that is counter-rotated relative to a fan (24). A planetary gearset (90) couples rotation of a fan (46) to an axial compressor rotor (46), such that the axial compressor r...
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WO/2006/059996A1 |
A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section (66), a hollow fan blade section (72) and a diffuser section (74). The hollow fan blade section defines a airflow p...
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WO/2006/059975A1 |
A tip turbine engine (40) provides a peripheral combustor (30) with a more efficient combustion path through the combustor and through the tip turbine blades (34) . In the combustor, the core airflow is received generally axially from co...
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WO/2006/059970A2 |
A gas turbine engine (10) provides a differential gear system (58) coupling the turbine (20) to the bypass fan (14) and the compressor (16). In this manner, the power/speed split between the bypass fan and the compressor can be optimized...
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WO/2006/059982A1 |
A controller is mounted remotely from a turbine engine and provided with an independent power source (120, 138). The controller may be an engine controller (112) generating control signals based upon user inputs and sensor inputs, or a f...
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