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WO/2008/091289 |
An instrumented component (18, 19) for use in various operating environments such as the hot gas path section of a combustion turbine engine (10). The component (18, 19) may have a substrate, a sensor (50, 204, 210) connected with the su...
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WO/2008/091289 |
An instrumented component (18, 19) for use in various operating environments such as the hot gas path section of a combustion turbine engine (10). The component (18, 19) may have a substrate, a sensor (50, 204, 210) connected with the su...
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WO/2008/087126 |
Method of Controlling a Fuel Split Method of controlling a fuel split of a pilot fuel flow and a main fuel flow in a gas turbine combustor in case of load reductions characterised in that the rate of change of fuel demand is monitored (1...
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WO/2008/080655 |
Thermally stressed components can be protected against excessive heat input by active cooling, or by applying thermal insulation layers. The invention increases said effect, by providing diagonally extending slots (19) in the surface (16...
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WO/2008/081487 |
A gas-turbine burner is provided with a first duct (18), in which fuel gas with low calorific value is supplied in use, and with a second duct (17), in which combustion air is supplied in use; the first and the second ducts (17, 18) are ...
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WO/2008/080639 |
The invention relates to a pressure measurement device (20) for pressure measurement in a combustion medium inside a gas turbine, which gas turbine contains a burner (10) for supplying the combustion medium in an uncombusted state to a c...
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WO/2008/077882 |
A burner for a gas turbine comprising a main burner (2) and a pilot burner, wherein the main burner (2) has a supporting structure (6), a heat shield (18) and a holder (8) for the heat shield (18), and wherein the holder (8) is at least ...
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WO/2008/078024 |
The invention relates to an environmental barrier for a substrate made of a composite material with a ceramic matrix containing silicon, essentially SiC, which is formed by an anti-corrosion protection layer containing an aluminosilicate...
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WO/2008/078024 |
The invention relates to an environmental barrier for a substrate made of a composite material with a ceramic matrix containing silicon, essentially SiC, which is formed by an anti-corrosion protection layer containing an aluminosilicate...
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WO/2008/071902 |
A fuel injector head (17) for a gas turbine engine the head comprising a pilot injector (10) and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bound...
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WO/2008/071756 |
A burner for a gas-turbine engine comprises a swirler and a combustion chamber. The swirler comprises a number of vanes arranged in a circle, each adjacent pair of vanes defining a flow slot for the flow of air and fuel into the swirler,...
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WO/2008/059045 |
A combustion apparatus includes a first combustor (A) connected to a second combustor (B) by way of a passage (30, 34), in which is disposed a swirler (32). The swirler may be of the axial (32) or radial (70, 100) type. The passage is or...
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WO/2008/057685 |
A combustor nozzle (72) is provided. The combustor nozzle includes a first fuel system (74) configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fue...
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WO/2008/057685 |
A combustor nozzle (72) is provided. The combustor nozzle includes a first fuel system (74) configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fue...
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WO/2008/052867 |
A system (S) for controlling nitrogen oxide (NOx) emissions and combustion pulsation levels of a gas turbine having a gas turbine combustion system comprising a single combustion chamber and multiple burners. The system (S) comprises a c...
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WO/2008/052830 |
A nozzle for a fuel injector, in particular for a gas-turbine engine, is provided comprising a planar conductive electrode (104) with a sharp edge forming an aperture; an upper insulation layer (102) above the electrode and a lower insul...
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WO/2008/049678 |
A burner, in particular a gas turbine burner, comprising at least one swirler (2), the swirler (2) having vanes (12) with vane walls delimiting external air passages (14) between the vanes (12) wherein at least one of the vanes (12) comp...
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WO/2008/051298 |
An improved system and method for controlling and directing sound waves is provided. A fuel-oxidant mixture is supplied to at least one detonator having at least one spark initiator. The fuel-oxidant mixture flows through the at least on...
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WO/2008/047825 |
[PROBLEMS] To provide a gas turbine combustor capable of performing stable heavy-load combustion in a small combustion chamber, a high combustion efficiency, and low CO and NOx concentrations. [MEANS FOR SOLVING THE PROBLEMS] This gas tu...
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WO/2008/049067 |
The invention relates to the use of a premising apparatus for gas and fuel in combination with energy release/conversion device of a type characterized by having a high intake velocity.
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WO/2008/049067 |
The invention relates to the use of a premising apparatus for gas and fuel in combination with energy release/conversion device of a type characterized by having a high intake velocity.
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WO/2008/040118 |
A fuel manifold for a gas turbine engine having a first peripheral surface having a first channel defined therein and a second peripheral surface having a second channel defined therein, each of the first and second channels being sealin...
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WO/2008/037554 |
A gas turbine engine includes a number of high-temperature modules, each of which includes a combustion unit and a transition duct. The modules are secured to the engine by means of a displacement mechanism, which enables rapid and easy ...
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WO/2008/037554 |
A gas turbine engine includes a number of high-temperature modules, each of which includes a combustion unit and a transition duct. The modules are secured to the engine by means of a displacement mechanism, which enables rapid and easy ...
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WO/2008/034227 |
A fuel manifold assembly (22) for a gas turbine engine (10) comprises an annular fuel manifold (21) and a plurality of fuel nozzles (30) circumferentially distributed about the fuel manifold (21). The fuel manifold (21) has at least one ...
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WO/2008/033542 |
A fuel injector (30) for a gas turbine engine (100) is disclosed. The fuel injector includes an injector housing (30a) having a longitudinal axis (98). The injector housing includes one or more fuel inlets (48, 54) one or more fuel galle...
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WO/2008/033542 |
A fuel injector (30) for a gas turbine engine (100) is disclosed. The fuel injector includes an injector housing (30a) having a longitudinal axis (98). The injector housing includes one or more fuel inlets (48, 54) one or more fuel galle...
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WO/2008/028621 |
Combustion chamber (1) for a gas turbine, with a flame tube (3) of the combustion chamber (1) having, in the flow direction, a mixing zone (15) for mixing a fuel with air to form a fuel/air mixture, as well as a primary combustion zone (...
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WO/2008/030214 |
An improved turbine spring clip seal (10) for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal (10) may include an inner housing (14) and an outer housing (12). The inner housing (14) or the outer...
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WO/2008/030214 |
An improved turbine spring clip seal (10) for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal (10) may include an inner housing (14) and an outer housing (12). The inner housing (14) or the outer...
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WO/2008/025525 |
A method of controlling the combustion in a combustion chamber with a combustion space is provided, wherein fuel in liquid form and oxidizer in liquid form are blown into the combustion space, wherein at least one control jet which influ...
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WO/2008/019969 |
A burner (1, 101), particularly for a gas turbine, with at least one nozzle pipe (7, 107) and a fuel fluid inlet pipe (9) being in connection with the nozzle pipe (7, 107) for feeding the fuel fluid into the nozzle pipe (7, 107), is prop...
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WO/2008/019997 |
Disclosed is a swirler passage (24) for mixing fuel and compressor air with at least two side walls (31); at least first and second conduits (14,15) arranged inside at least one of the at least two side walls, the first conduit forming a...
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WO/2008/017551 |
The invention relates to a combustion chamber of a combustion plant, in particular a gas turbine, with a heat shield (1) comprising at least two segments (2, 2'). Each of the segments (2, 2') has a liner element (4, 4´) facing a combust...
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WO/2008/017550 |
The invention relates to a combustion chamber (3) of a combustion installation, the combustion chamber (3) having a heat shield (1) with at least two segments (2) and (2'). Each of the segments (2) and (2') has a liner element (4, 4') fa...
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WO/2008/017551 |
The invention relates to a combustion chamber of a combustion plant, in particular a gas turbine, with a heat shield (1) comprising at least two segments (2, 2'). Each of the segments (2, 2') has a liner element (4, 4´) facing a combust...
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WO/2008/009729 |
Provided is a burner having a device (14) for supplying the burner with a fuel fluid, which device (14) has at least one opening (16) through which fuel fluid can emerge. The device for supplying the burner with a fuel fluid has a piezoe...
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WO/2007/144209 |
A burner, in particular a gas turbine burner, comprises: - at least one swirler (2), the swirler (2) having at least one air inlet opening, at least one air outlet opening positioned downstream to the air inlet opening and at least one s...
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WO/2007/145607 |
A transition duct (122) for routing a gas flow from a combustor (124) to the first stage (126) of a turbine section in a combustion turbine engine has an internal passage from an inlet (140) to an outlet (142) that is offset from the inl...
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WO/2007/141091 |
The invention relates to a machine component with a base (40) made of a base material, a part of the surface of which has been equipped with armor-plating (42), made of a plating material with greater hardness in comparison to the base m...
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WO/2007/137883 |
The invention relates to a combustion chamber wall in a combustion chamber (15), comprising a support structure (18) with a number of heat shields which are attached to the support structure (18) with the aid of a fastening means. Said f...
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WO/2007/131818 |
Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a plurality of vanes arranged in a circle, flow slots being defined between adjacent vanes in the circle, each flow slot having an inlet end and a...
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WO/2007/122110 |
A gas turbine pre-mix combustion system is provided which comprises : - at least one combustor (1) with a combustor wall (3) which partly surrounds a combustion zone; - at least one mixing duct (9) including an air passage which leads to...
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WO/2007/122040 |
The invention relates to a blade (20) for a turbine comprising a blade wall (30, 32), a first channel (36) for guiding a first medium (M1) and a second channel (38) for guiding a second medium (M2) that can be supplied to the turbine bla...
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WO/2007/122040 |
The invention relates to a blade (20) for a turbine comprising a blade wall (30, 32), a first channel (36) for guiding a first medium (M1) and a second channel (38) for guiding a second medium (M2) that can be supplied to the turbine bla...
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WO/2007/119115 |
One embodiment is a gas turbine engine premix injector (200) including a mixing duct (214), a plurality of air inlet slots (216) leading to the duct, a plurality of gaseous- fuel inlet apertures (222) leading to the duct, a plurality of ...
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WO/2007/119115 |
One embodiment is a gas turbine engine premix injector (200) including a mixing duct (214), a plurality of air inlet slots (216) leading to the duct, a plurality of gaseous- fuel inlet apertures (222) leading to the duct, a plurality of ...
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WO/2007/115989 |
A gas turbine combustor (1) is provided, which comprises: - a combustion chamber (5, 105, 205, 305) having an axial direction and a radial direction; - air passages (17, 127, 128, 217, 317) for feeding an air stream into the combustion c...
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WO/2007/113130 |
The invention relates to a burner (1) for a gas turbine, comprising at least one burner housing (3) projecting into a combustion chamber (2) and having a premix zone (4) and a lance (5), at least partly projecting into the premix zone (4...
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WO/2007/113054 |
The invention relates to a burner arrangement (20) having a conical swirl body, arranged concentrically to a burner axis (21), in the form of a double cone (11) which encloses a swirl space (17), and having a central fuel lance (12) whic...
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