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WO/2003/027361 |
A gas turbine component consists of a superalloy base material with a single crystal structure and a protective MCrAlY-coating (6). The MCrAlY-coating (6) has a g/g' single crystal structure, which is epitaxial with the base material. It...
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WO/2003/025466 |
The invention is a method in which a rich fuel/air mixture (12) comprising a first fuel contacts a catalyst (16) to create a product stream (22) such that mass transfer to the catalyst surface limits the rate of catalytic reaction. The c...
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WO/2003/023281 |
The invention relates to a damping arrangement for reducing resonant vibrations in a combustion chamber (1) comprising a combustion chamber wall (2), which is provided with a double wall and encloses a space (3) in a gas-tight manner wit...
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WO/2003/021084 |
The invention relates to a gas turbine (1) having a combustion chamber arrangement and a turbine chamber (2) connected downstream of said combustion chamber arrangement, wherein the combustion chamber arrangement includes a plurality of ...
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WO/2003/021149 |
The invention relates to a combustion chamber arrangement (1) for a gas turbine, with a number of individual combustion chambers (3) which open into an annular gap (13), leading to a turbine chamber (2), whereby burners (6) are arranged ...
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WO/2003/021150 |
The present additional control strategy has been developed to allow the gas turbine to operate at lower load or at other conditions where the total fuel required by the gas turbine is not optimum for full combustion of the fuel. The pres...
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WO/2003/016695 |
A plate−like body joining method free from degradation in various functions including cooling is provided. A plate−like body joining method for joining at least two plate−like bodies with a flow channel extending along at least one...
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WO/2003/014621 |
The invention relates to a pre-mix burner (1) with a main burner (3) and a pilot burner (5), for stabilisation of the main burner (3). The pilot burner (5) comprises a fine-pored burner material (41), which permits a combustion with low ...
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WO/2003/010426 |
A gas turbine engine adapted for use with a range of fuels has a compressor stage, a combustion stage (14) and a turbine stage (10) with an air inlet arrangement from the compressor stage arranged in an annular form and having a variable...
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WO/2003/010431 |
A rotary ramjet engine is providing operating with a very low axial flow component. The engine has a rotor (70), shaft (28), a plurality of ramjet combustors mounted on the periphery of the rotor (70). A set of spaced helical strakes ext...
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WO/2003/008791 |
A combustion liner (30) utilizes a plenum (31) for containing cooling air and for reintroducing it into the combustor (35). The plenum is enlarged to increase the amount of cooling air contained. To install the liner assembly into the co...
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WO/2003/008768 |
The invention relates to a method for operating a burner (7) of a gas turbine (2), whereby a fossil fuel (B) is gasified and the gasified fossil fuel (B) is fed as synthesis gas (SG) into the burner (7) for combustion, said burner being ...
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WO/2003/006883 |
The invention pertains to a coolable segment (1) for a turbo machinery (20), which turbo machinery (20) is operated with a hot fluid (29). The segment (1) comprisesa cooling wall (2) extending in an axial direction (37) and in a circumer...
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WO/2003/006884 |
A method of combustor cycle air flow adjustment for a gas turbine engine to solve the problem of a higher flame temperature in the combustor, affecting the emission levels when a heat-recuperated air flow cycle is used to increase the co...
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WO/2003/006887 |
A premixing nozzle (800) has a swirler vane (300) in a nozzle barrel (10) for stirring combustion air. The swirler vane (300) is attached at one end thereof to the nozzle barrel (10) and connected at the other end to a hub (100). The fro...
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WO/2003/006888 |
A cyclone combustor (10) uses a novel pre-mixture injection scheme to optimize performance. The cyclone combustor includes a cylindrical combustor can (12) and three fuel/air premixing tubes (30) entering the combustor can radially, with...
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WO/2003/006889 |
An air handling system (10) containing sections each having a framework made up of tubular structural elements defining each perpendicularly aligned openings each (11) of which shares a common structural element with its neighbors (11). ...
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WO/2003/006885 |
A swirled diffusion dump combustor of the present invention includes a cylindrical combustor can and a fuel and air mixer attached to the upstream end of the combustor can. The mixer is generally formed by an annular chamber which is def...
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WO/2003/006886 |
A fuel and gas mixer for a gas turbine combustor includes a body member. The body member has a truncated conical annulus, with its smaller end which communicates with a smaller end of a downstream truncated conical chamber. Gaseous fuel ...
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WO/2003/002913 |
A gas turbine combustor, wherein a ring (100) forming a cooling air layer is fitted to a combustion chamber inner tube (11), cooling air fed from a compressor through a cooling air supply hole (41) is supplied to the ring, and the coolin...
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WO/2003/002914 |
A flanged hollow structure capable of increasing a structural integrity by preventing cracking due to thermal fatigue from occurring around a flange, comprising the annular flange fixed to the outer peripheral surface thereof causing a t...
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WO/2003/001042 |
A wear reduction means for a fuel nozzle interface of an industrial gas turbine combustor (10) is disclosed. The wear reduction means includes a replaceable insert (47) welded into to the engagement location (45) of the fuel nozzle tip (...
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WO/2003/001118 |
A bypass valve capable of being normally operated by smoothly rotating a grid plate irrespective of the driving state of a gas turbine, comprising a frame installed so as to close a plurality of annular arranged compressed air inlets and...
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WO/2002/103176 |
The invention relates to a method for decreasing the level of carbon dioxide in the fumes emitted by a power generator which combusts a mixture of a combustive agent and a fuel containing hydrocarbons. According to the inventive method, ...
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WO/2002/101294 |
The invention relates to a combustor comprising an air flow channel for feeding air into the interior, and a fuel nozzle disposed in the air flow channel and having a spout port for spouting fuel, wherein a turbulence generating body adj...
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WO/2002/099337 |
A head part of an annular combustor for a gas turbine engine according to the present invention includes an annular bulkhead at the upstream end of the combustor. The bulkhead includes a first annular section integrally, inwardly and rad...
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WO/2002/097332 |
The invention relates to a heat shield arrangement (5) for a hot gas conducting structure, in particular a metal component of a gas turbine unit or combustion chamber (10), with heat shield elements (20) anchored adjacently on a support ...
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WO/2002/095293 |
The invention relates to a burner apparatus (1) for burning fuel (5) with air (4) to combustion gas, in particular within a combustion turbine, comprising a premixing chamber (3) for premixing fuel (5) and air (4) with. The premixing cha...
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WO/2002/090831 |
The invention relates to a device for injecting a liquid fuel in a pressurised air flow (7), in particular for a combustion chamber. The inventive device comprises: a hollow cylindrical body (10) with a longitudinal axis (YY') which defi...
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WO/2002/088604 |
A gas turbine is provided which has a combustor comprising a plurality of can-type combustor elements and an annular element. Isolated combustion takes place in the can-type combustor thereby generating individual component hot gas strea...
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WO/2002/088603 |
A combustion system for a gas turbine engine includes a Catalyst (CAT) combustion sub-system for generating combustion products under a lean premixed fuel/air condition in the presence of a Catalyst and a Dry-Low-Emissions (DLE) combusti...
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WO/2002/088601 |
The invention relates to a combustion chamber (5), in particular of a gas turbine, comprising an external wall structure (10) that surrounds an internal area (8) and an internal wall, which is formed by the surface of a housing (15) that...
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WO/2002/088602 |
A combustion system for a power generating gas turbine engine which includes at least a combustion chamber with a annular fuel manifold at one end of the combustion chamber and a passageway having a narrow throat downstream of the fuel m...
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WO/2002/083281 |
A delivery system for generating a sparging gas containing catalyst particles and delivering them to a flame zone (62) of a combustion reaction is disclosed. A catalyst mixture receptacle (2) for the delivery system includes a floating b...
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WO/2002/084176 |
The present invention relates to a device for increasing heat power of a gas burner, and an object of the present invention is to provide a device for increasing heat power of a gas burner, capable of improving heat efficiency by making ...
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WO/2002/075211 |
A segmented (A, B, C) radiant burner permits modulation of thermal output by independent control of fuel gas flow (66, 67, 68) to each segment. The burner features a porous fiber burner face (54)optionally having dual porosities, and a m...
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WO/2002/073091 |
A burner comprising a plurality of combustion channels (A1, A2) for supplying fuel (G) to air (A) flowing through the channel and supplying a combustion section (15) with mixture gas for combustion, wherein each combustion channel (A1, A...
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WO/2002/073090 |
Method and apparatus for control of Zeldovich (thermal) NOx production in catalytic combustion systems during combustion of liquid or gaseous fuels in the post catalytic sections (14) of gas-turbine combustors by reducing combustion resi...
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WO/2002/073089 |
A fuel injector for a gas turbine is disclosed which includes a nozzle body having a discharge portion defining a discharge orifice, the discharge portion including a fuel circuit for directing a hollow fuel film toward the discharge ori...
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WO/2002/068867 |
A method of controlling a catalytic combustion system comprising a flme burner or a heat exchanger, a fuel injector positioned downstream of the flame burner or heat exchanger and a catalyst positioned downstream of the fuel injector, wh...
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WO/2002/066898 |
The invention relates to combustion chambers of gas-turbine engines, in particular engines provided with flame control units including the combustion chambers of the gas-turbine engines for afterburning. Said invention is characterised i...
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WO/2002/063156 |
An improved bulkhead for dual industrial and aero gas turbines with annular or can combustors that may be formed by one or more bulkhead elements (10). Each element has a fuel-air channel (12) havig an air inlet (11) and a fuel-air mixtr...
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WO/2002/061339 |
A premix burner is disclosed, in which air and fuel may be mixed to give a fuel/air mixture, for the formation of at least one stable flame front, within a combustion chamber arranged downstream, for driving a gas turbine arranged after ...
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WO/2002/055754 |
The invention relates to a method and a device for gas phase diffusion coating of components (3), wherein a component surface (4) which is to be coated is brought into contact with a metal halogenide as a coating gas, forming a diffusion...
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WO/2002/052201 |
The invention relates to a burner, essentially consisting of a swirl generator (9) for a combustion air stream (22, 23), a swirl chamber (26) and elements (1-8,11-18, 24, 25) for introducing fuel into the combustion air stream (22, 23). ...
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WO/2002/052194 |
An ultrasonically enhanced continuous flow apparatus for injection of liquid fuel into a continuous fuel combustor and a method of improving continuous flow fuel combustors by the application of ultrasonic energy to a pressurized liquid ...
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WO/2002/052134 |
A fuel/air premixer (16) for an industrial type gas turbine combustor (10) wherein the premixer (16) includes a diffuser ring assembly (20) made up of annular concentric rings (22) and upstream of the diffuser ring assembly (20) in the a...
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WO/2002/048610 |
The invention concerns a catalytic combustion device comprising a main combustion zone (20, 200) including at least a catalytic section (5, 103) and at least an air/fuel mixing zone (11, 117), said mixing zone comprising at least a press...
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WO/2002/048527 |
The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure thro...
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WO/2002/038920 |
A support structure (100) for being disposed within an outer containment comprising: a center (104); at least two branched segments oriented about the center and encompassed by an outer perimeter; wherein each branched segment includes: ...
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