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WO/2006/059979A1 |
A tip turbine engine assembly includes an engine support structure with a rear case, exit guide vanes, an exhaust mixer, and engine mounts. The rear case is disposed about an engine centerline. The exit guide vanes extend radially inward...
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WO/2006/060000A1 |
A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine roto...
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WO/2006/059974A1 |
A gearbox assembly (90) closely couples a fan-turbine rotor assembly (25) and an axial compressor rotor (46) to reduce the overall engine length and minimizes the number of engine bearings.
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WO/2006/059993A1 |
A tip turbine engine (10) provides first and second turbines (32) rotatably driven by a combustor (30) generating a high-energy gas stream. The first turbine (32) is mounted at an outer periphery of a first fan (24a) , such that the firs...
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WO/2006/059973A1 |
A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a portion of the fan bypass airflow which enters...
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WO/2006/059971A2 |
A tip turbine engine assembly includes an integral engine outer case (8) located radially outward from a fan assembly (30). The integral outer case (8) includes a rear portion (124) and a forward portion (128) with an arcuate portion (13...
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WO/2006/059977A1 |
A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extend...
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WO/2006/060013A1 |
A seal assembly (118) mounted within a nonrotatable static inner support structure (16) for engagement with an axial seal face surface (114) and a radial seal face surface (116). The radial seal (120) engages the axial seal face surface ...
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WO/2006/059980A2 |
A fan-turbine rotor assembly includes a diffuser section (114) which turns and diffuses the airflow from a radial core airflow passage (80) toward an axial airflow direction. Diffuser flow passages communicate with the diffuser passages ...
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WO/2006/059986A1 |
A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or reducing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result...
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WO/2006/059994A1 |
A seal assembly (116) mounted within a rotationally fixed static outer support structure (14) for engagement with an annular seal face surface (172) located upon a fan-turbine rotor assembly. The seal assembly provides minimal leakage of...
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WO/2006/059990A1 |
A fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is com...
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WO/2006/060009A1 |
A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage betw...
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WO/2006/060012A1 |
A tip turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. Assembly of a multitude of turbine blade clusters to a ...
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WO/2006/059991A1 |
A fan-turbine rotor assembly of a tip turbine engine includes a multitude of turbine blades which each define a turbine blade passage which bleed air from a diffuser section to provide for regenerative cooling. Regenerative cooling airfl...
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WO/2006/059749A1 |
A gas turbine apparatus (2) has an air compressor (20) for compressing air, a combustor (21) for combusting the compressed air, a turbine (22) rotatable by a gas discharged from the combustor (21), and a recuperator (23) for exchanging h...
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WO/2006/060006A1 |
A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) in the aft portion of the tip turbine engine. T...
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WO/2006/060011A1 |
A non-rotating compartment along an engine centerline of a tip turbine engine is defined between an inner support housing, an outer support housing and an aft housing. The non-rotating compartment provides a space that may be utilized fo...
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WO/2006/059992A1 |
A fan-turbine rotor assembly for a tip turbine engine includes an inducer with an inducer inlet section and an inducer passage section in communication with a core airflow passage within a fan blade. Each inducer inlet section is canted ...
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WO/2006/060002A1 |
A fan-turbine rotor assembly includes a multitude of fan blades, which each includes an inducer section (66), a hollow fan blade airfoil section (73) and a diffuser section (74). A rib (120) located within the airflow passage (80) connec...
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WO/2006/059981A1 |
A hydraulic seal (170) for a tip turbine engine includes an inner radial flange (171) and an outer radial flange (172). The inner radial flange (171) rotates relative the outer radial seal section and the planet carrier face (94) to prev...
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WO/2006/059969A1 |
A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54). The compressor case (50) is directly driven by the rotation of t...
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WO/2006/060010A1 |
A tip turbine engine (30) includes a low pressure compressor (22) having a plurality of inlet guide vanes (55) that are mounted at an inlet to the compressor case (50). Each inlet guide vane (55) includes at least one fluid outlet (56) p...
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WO/2006/059987A1 |
A particle separator (20) for a tip turbine engine (10) includes a generally conical inclined leading surface (24) leading to a maximum radius (25) and a tapered trailing surface (56) having a radius at all points therealong less than th...
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WO/2006/059976A1 |
A turbine engine includes at least one rate sensor mounted adjacent a fan rotor assembly. The sensor measures a rate of rotation of the fan rotor assembly by detecting the temporary proximity of a portion of the fan rotor assembly during...
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WO/2006/059978A1 |
A tip turbine engine (10) according to the present invention includes an engine support structure (12) for cantilevering a load bearing shaft from an engine support plane (P). An engine support structure (12) defines the engine support p...
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WO/2006/060005A1 |
A fan-turbine rotor assembly for a tip turbine engine includes a fan hub with an outer periphery scalloped by a multitude of elongated openings which extend into a fan hub web. Each elongated opening defines an inducer section and a blad...
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WO/2006/059988A1 |
A tip turbine engine assembly includes a compressor module (12) and a fan module (14) located aft of the compressor module (12). The compressor module (12) and fan module (14) are fastened together along a mating portion with seals that ...
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WO/2006/059985A1 |
A tip turbine engine (10) according to the present invention provides at least one gear (90) coupling rotation of a bypass fan (24) to an axial compressor (22), such that the axial compressor (22) is driven by rotation of the fan (24) at...
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WO/2006/046722A1 |
A gas turbine apparatus (1) has an air compressor (20) for compressing air, a combustor (21) capable of combusting the air compressed by the air compressor (20), and a first fuel supply system (24) configured to supply a fuel to the comb...
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WO/2006/046976A2 |
A turbine engine system and a method for using the turbine engine system that includes at least one low-pressure compressor (205), at least one high-pressure compressor (225), at least one low-pressure turbine (245), and at least one hig...
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WO/2006/043734A1 |
There is provided a micro power generating device. A compressor impeller and a turbine wheel are coupled to the ends of a rotating shaft. A cooler is provided for lowering a temperature of the compressed air from the compressor impeller....
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WO/2006/041760A2 |
A power augmentation method for a gas turbine (1) in which water is injected into one or more stages (22, 24, 26, 28) of an auxiliary compressor (2) to produce a vapor containing gas stream (20). The vapor containing gas stream (20) is a...
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WO/2006/040268A1 |
The invention relates to a method for operation of a burner (13), whereby a fuel (15) is supplied to the burner (13), sprayed into the combustion air (7), mixed with the combustion air (7) to give a fuel/air mixture and burnt in a combus...
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WO/2006/042006A2 |
Disclosed is hydrogen storage processes and assemblies using metallized halloysite or metalized lipids. The addition of metals or metal salts increases the hydrogen storage ability of the halloysite or lipids relative to their non-metall...
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WO/2006/038879A1 |
The invention relates to a gas turbine intermediate structure (14) for being arranged between a first and a second gas turbine structure (8 and 9) in an axial direction (18) of a gas turbine (1). The intermediate structure (14) comprises...
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WO/2006/035522A1 |
A gas turbine apparatus, a low calorie content gas feeding apparatus capable of feeding a low calorie content gas as a fuel for gas turbine stabilized by suppressing the sudden rise of its calorie content, and a method of suppressing the...
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WO/2006/029888A1 |
Convex sealing bottom (10) for a twin-shaft turbine of the type comprising a series of convex disks constrained to each other by means of a series of pins, each disk of said disks comprises an outer shaped edge which is engaged with a co...
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WO/2006/030255A1 |
A four-stroke endothermic engine with a rotating drum, essentially consisting of a drive shaft (1) onto which a cylindrical drum (9) equipped with fixed radial blades is fitted, said shaft (1) being rotatable inside a stationary body (11...
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WO/2006/026862A1 |
A combustor (16) for a gas turbine (10) engine includes a sheet metal combustor wall (22) having a plurality of cooling apertures (34) therein immediately upstream of a corner (24) between two intersecting combustor wall portions (33/32,...
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WO/2006/021098A1 |
A gas turbine engine combustor (16) comprises a heat shield-less combustor design in which a plurality of holes (46, 46’) are provided in the dome portion of the liner itself (34, 34A, 34B), which holes are adapted to direct air into t...
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WO/2006/019131A1 |
A volatile organic compound is treated to make it harmless and, in addition, the overall energy efficiency in a facility where the treatment of a volatile organic compound is necessary is heightened. A discharge gas containing a volatile...
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WO/2006/018389A1 |
The invention relates to a method for generating energy in an energy generating installation (10) comprising a gas turbine (12). According to said method, in a first step, a gas containing oxygen is compressed in a compressor (13, 14) of...
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WO/2006/016211A1 |
A power generation system (2) includes a gas generator (20) configured to receive an oxygen stream (12) and a gaseous hydrocarbon fuel stream (14) at an inlet of the gas generator, and a turbine section (24) disposed downstream from the ...
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WO/2006/010200A1 |
A turbine engine (10) comprising an engine body (3) disposed within a nacelle (2) and extending from adjacent the inlet end of the nacelle (2) to adjacent the outlet end (7) of the nacelle (2). The engine body (3) housing a combustion ch...
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WO/2006/004141A1 |
A heat exchanger packed with a catalyst for reforming DME is installed in the discharge line of a combustion apparatus such as a furnace, an internal combustion engine or electric power generation facilities. A mixed gas from DME and H2O...
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WO/2005/119028A1 |
The invention relates to a gas turbine compression system (1) comprising a gas channel (5), a low pressure compressor section (8) and a high pressure compressor section (9) for compression of the gas in the channel and a compressor struc...
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WO/2005/108757A2 |
A turbocharger (24) comprising a turbine (28), director (2), and compressor (34). The turbine (28) may be formed as a turbine wheel (68) surrounded by at least two scrolls (26). The at least two scrolls (26) may direct exhaust gases supp...
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WO/2005/108759A1 |
An apparatus and method is provided for improving efficiency of a transonic gas turbine engine compressor (20) by bleeding off a shockwave-induced boundary layer from the gas flow passage (42) of the compressor using an array of bleed ho...
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WO/2005/106224A1 |
A process for producing electrical power including the step of: a) combusting a stoichiometric amount of a reactant in air in the presence of atomized water to obtain a gaseous mixture having a terminal temperature less than a maximum op...
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