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WO/2018/143168A1 |
This combustion device (C) uses fuel air to combust a fuel within a combustion chamber (N), wherein the combustion device comprises a reducing agent injection device for injecting a reducing agent toward a flame within the combustion cha...
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WO/2018/144008A1 |
A combustor for a combustion turbine engine incorporates a fuel and air premixer, embodiments of which locally vary structure of one or more of air ducts, fuel delivery passages, fuel and air mixing ducts, and/or fuel and air discharge d...
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WO/2018/144064A1 |
An air-cooled panel (200) for a combustion turbine engine includes, a first planar, metallic sheet (202), having an outer side and an opposed inner side. A monolithic, three-dimensional lattice structure (210), having a first face, is bo...
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WO/2018/139131A1 |
A natural gas fired combined-cycle power generation system is provided with: a vaporization device, a cooling device, a circulation flow path, a pump, and a gas-turbine combined power generation device. The vaporization device includes: ...
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WO/2018/140173A1 |
Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turb...
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WO/2018/140135A1 |
Gas turbine engines, as well as outer walls and flow path assemblies of gas turbine engines, are provided. For example, an outer wall of a flow path comprises a combustor portion extending through a combustion section, and a turbine port...
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WO/2018/137895A1 |
The invention relates to a fastening screw (26) for a heat shield element (14b) which is provided for use in a combustion chamber (4) of a gas turbine (1), comprising a screw shank (28) and a screw head (30). Arranged in the region of th...
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WO/2018/140136A1 |
Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including ...
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WO/2018/134501A2 |
The invention relates to a turbomachine combustion chamber, configured to be housed in a chamber housing of said turbomachine, which housing is provided with an air supply, said combustion chamber being delimited by at least a first subs...
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WO/2018/134058A1 |
The invention relates to a burner tip (19) for installation in a burner (11), wherein the burner tip (19) has a surface (OF) facing a combustion chamber (BR), an air channel structure (21) leading to the surface (OF) and defining an air ...
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WO/2018/133292A1 |
A nozzle with adjustable inner and outer flow channel equivalence ratios comprises a central cylinder (6), an outer-wall cylinder (3), and a wave swirler (5). The wave swirler (5) is coaxially disposed in the outer-wall cylinder (3). The...
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WO/2018/132241A1 |
The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle incl...
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WO/2018/132185A1 |
A field configurable support housing assembly (10) is provided. The support housing assembly comprises a support housing base (20) and a cylindrical hollow fuel rocket (40). The support housing base (20) includes at least one through hol...
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WO/2018/130765A1 |
The invention relates to a combustion chamber (6) for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine, comprising: - a radially outer annular shroud (11), - a radially inner annular shroud (12), coaxia...
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WO/2018/131142A1 |
This embodiment of a transition piece introduces combustion gas that is generated inside a liner inner tube of a combustor liner, which has a double pipe structure comprising the liner inner tube and a liner outer tube, into a turbine. T...
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WO/2018/131654A1 |
This control system regulates the flow rate of heating water supplied to a fuel heating device which heats gas turbine fuel, to control the temperature of the fuel supplied to a combustor of a gas turbine via the fuel heating device. The...
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WO/2018/127471A1 |
The invention relates to a burner tip (19) for a pilot burner, which can be used for example in a gas turbine. The invention also relates to a method for additively producing a burner tip (19) of this kind for example by means of selecti...
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WO/2018/128599A1 |
A gas turbine engine (10) has a combustor basket (15) that has resonators (25). Resonator bases (26) are attached directly to the outer surface (22) of a combustor liner (20). A thermal barrier coating (23) is applied to the internal sur...
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WO/2018/128600A1 |
A gas turbine engine (10) has a side seal (25a) located between adjacent exit pieces. The side seal (25a) comprises a first seal side (23a) and a second seal side (24a) that contact each other. The first seal side (23a) has a spring (26a...
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WO/2018/118466A1 |
A fuel manifold (10) configured to form a base support structure (12) to support a plurality of fuel nozzles (14) including a pilot fuel nozzle is provided. The fuel manifold may include stage fuel galleries (16, 18), and fuel feed bosse...
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WO/2018/116975A1 |
The present invention provides a plurality of main nozzles (34) of a combustor, the main nozzles (34) being provided spaced apart in a circumferential direction on an outer circumferential side of a pilot nozzle. The main nozzles (34) ea...
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WO/2018/118282A1 |
A combustion liner or component produced through the use of additive manufacturing techniques. The combustion liner or other component may be formed having a feature based optimized cooling circuit at least partially embedded in the thic...
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WO/2018/114918A1 |
The invention relates to a burner tip (19), suitable for use in a pilot burner, e.g. in a gas turbine. The invention further relates to a method for producing the burner tip (19) by an additive production process such as selective laser ...
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WO/2018/111558A1 |
A fuel distribution manifold (330) for a gas turbine engine (100) is disclosed herein. The fuel distribution manifold (330) includes a manifold body (331), a stage divider (332), and a plurality of manifold outlet ports (301-312). The st...
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WO/2018/094536A1 |
The present disclosure generally relates to rotary turbomachinery methods and integrated processes requiring high-energy efficiency. In one embodiment, the present invention relates to rim-rotor configurations enabling long-term survival...
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WO/2018/098157A2 |
A fuel burner includes a tube extending from a first end to a second end and having an outer surface and an inner surface defining a central passage. The central passage is supplied at the first end with a mixture of air and combustible ...
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WO/2018/090383A1 |
A nozzle (12) of a combustion chamber of a gas turbine engine, the nozzle comprising: a main nozzle member (20) forming an internal fuel gas channel (24) and a fuel gas outlet (26) in fluid communication with the fuel gas channel (24). T...
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WO/2018/090384A1 |
A combustion chamber of a gas turbine engine. The combustion chamber comprises: an annular flame pipe (10), wherein the annular flame pipe (10) forms an annular combustion cavity (14), and the annular combustion cavity (14) defines an ax...
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WO/2018/087878A1 |
A combustor liner (11) that is used in a gas turbine combustor and that forms a combustion chamber (13) is provided with: an outside wall (21) that is made of a metal material; a panel (25) that is made of a ceramic matrix composite and ...
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WO/2018/088184A1 |
The gas turbine plant is provided with a gas turbine (10), a heating device (60), a decomposition gas line (70), and a decomposition gas compressor (85). The heating device (60) heats ammonia so that the ammonia is pyrolyzed and decompos...
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WO/2018/082538A1 |
A method of optimizing a premix fuel nozzle (12) for a gas turbine is provided. When the gas turbine is in operation, the nozzle (12) comprises an axial flow field of air and fuel mixture flowing through a burner tube (25) and around a n...
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WO/2018/082539A1 |
A nozzle tip (24) for a premix fuel nozzle (12, 22) is provided. The nozzle tip (24) includes an outer body (26) having an outer body external face (36) facing the downstream end of a burner tube (25). The outer body external face (36) h...
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WO/2018/084943A1 |
A combustor of an industrial gas turbine engine having a combustor secured within a combustor casing with a combustor cavity surrounding the combustor, and a flow liner forming a cooling air space between the casing and the flow liner in...
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WO/2018/080474A1 |
A liner (10) for a gas turbine engine is inserted into a channel (12) located in a inlet ring (11) of a transition duct (8). The liner is formed as a flat unitary piece with angled ends (14). The angled ends complement each other. When i...
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WO/2018/078350A1 |
A gas turbine engine (1) has a centrifugal compressor (4) and a radial turbine (14) mounted to a turbine shaft (2) for rotation with the shaft about the shaft axis Z. A number of combustion chambers (10) in the air/gas flow path between ...
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WO/2018/075854A1 |
An apparatus for assisting with the combustion of fuel includes a swirler assembly and a fuel nozzle. Fuel from a fuel nozzle fuel reservoir is directed into a fuel nozzle mixing zone and combines with air inside the fuel nozzle mixing z...
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WO/2018/072970A1 |
The invention relates to an improved ceramic heat shield (155) for a gas turbine (100). The ceramic heat shield (155) has a porous ceramic body (11) and according to the invention an infiltration coating (12) that is provided in a surfac...
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WO/2018/071260A1 |
A gas turbine engine includes a compressor section and turbine section. The gas turbine engine of the present disclosure is a relatively small gas turbine engine, configured to generate less than 1491 kW (2,000 horsepower) during peak op...
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WO/2018/068980A1 |
The invention relates to a heat shield element (01) for use in a heat shield of a combustion chamber. The heat shield element (01) comprises a ceramic tile element (11) and a metallic carrier element (31). For fastening purposes, the til...
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WO/2018/067253A1 |
A combustion management device for generating a thrust burst to impart a physical impulse. In operation, a combustion chamber, defined by a valve unit (33), is primed to a set pressure and fueled by fuel injectors (23). An ignitor (22) t...
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WO/2018/060200A1 |
Cooled machine component, particularly a turbomachine component, comprising a body (2) with at least one integrated cooling channel (40) for guiding a cooling fluid through an interior of the body, the cooling channel comprising a lattic...
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WO/2018/059804A1 |
The invention is related to a gas turbine arrangement for at least dual fuel operation, comprising a plurality of fuel manifolds (21,22,23), each connected to each of at least one combustor (12) and a control system (17). A first manifol...
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WO/2018/060054A1 |
A method for controlling pilot-fuel/pilot-air ratio provided to a burner of a combustion system for altering its operating point is presented. First, a value of a first parameter e.g. temperature, is checked, and if the value equals or e...
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WO/2018/060098A1 |
A pilot burner assembly for a combustion volume in a gas turbine engine is presented. The pilot burner assembly includes a pilot burner, a pilot-fuel supply line, and a pilot-air supply line. The pilot burner has a burner face that inclu...
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WO/2018/063151A1 |
A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air f...
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WO/2018/060044A1 |
A swirler for creating a swirling fuel/air mix is presented. The swirler has vanes extending radially around a central axis of the swirler and positioned on an annular base. The swirler has mixing channels for mixing the fuel and the air...
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WO/2018/056994A1 |
A turbine engine can have an atomizer having two orifices that form an intersecting spray cone. The turbine engine can also have an atomizer that has three orifices that forms a partially filled spray cone. The intersecting sprays cones ...
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WO/2018/055325A1 |
A combined combustor and recuperator is formed with the recuperator surrounding the combustor. Cold gas conduits (14, 16, 20) through the recuperator follow along involute paths toward the combustor. Hot has conduits (26) through the rec...
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WO/2018/054918A1 |
A pilot burner assembly for a combustion chamber in a gas turbine engine is presented. The pilot burner assembly includes a pilot burner and a radial swirler. On a burner head face of the pilot burner, pilot fuel injection holes are pres...
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WO/2018/050999A1 |
The invention relates to a combustion chamber (40) for a turbine engine which comprises an annular wall (12) defining an inner space (11) of the chamber, a film of wall-cooling air (28) along the annular wall (12) in the inner space, com...
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