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WO/2015/009396A1 |
A cover (54, 54A-B) enclosing with clearance (65) an acoustic damping resonator (24) on a working gas path liner (22) of a gas turbine component (28). The cover includes a coolant inlet chamber (56, 56B) with a top wall (58, 58B) that is...
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WO/2015/004642A1 |
A gas turbine combustion chamber includes a casing (2), a plurality of thermally insulating tiles (7) and at least one reversible fastening device (10), which fixes one of the respective tiles (7) to an inner face (3a, 4a) of the casing ...
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WO/2015/001517A1 |
A tile for covering combustion chambers, in particular for gas turbine energy production power plants, is provided with a main body (23), which extends along a longitudinal axis (B) and is provided with: • a main face (24), which faces...
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WO/2015/002686A2 |
A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a hemi-spherical protuberance.
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WO/2014/207207A1 |
The invention relates to a heat shield (2) with a support structure (28) and a number of heat shield blocks (20, 22), said heat shield blocks being secured to the support structure (28) and having a cold side (26) facing the support stru...
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WO/2014/210402A1 |
A combustor apparatus defining a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus comprises an outer wall including a fuel inlet opening for receiving a fuel feed pipe....
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WO/2014/204449A1 |
A gas turbine combustor assembly (200) includes a fuel injector (204), a dome stator (220) around the fuel injector (204), and a dome sleeve (222) coupled to the dome stator. The dome sleeve (222) defines an air inlet opening (268) with ...
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WO/2014/201249A1 |
A panel for a combustor of a gas turbine engine includes a cold side defining at least one convex portion and at least one concave portion. The concave portion is in communication with a passage. A method of operating a combustor section...
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WO/2014/200588A2 |
A combustor of a gas turbine engine includes an additively manufactured liner panel with a heat transfer augmentation feature.
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WO/2014/201135A1 |
A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10% - 35% of a combustion airflow. A radial fuel inject...
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WO/2014/200580A1 |
A single, unitary fuel/oil manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various fuel system and lubricating system compoents directly to the fuel/oil manifold. The fuel/oil manifold al...
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WO/2014/197070A2 |
A swirler assembly for a gas turbine engine includes an outer annular injector which at least partially surrounds an inner injector and an air-assist atomizer upstream of said inner injector.
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WO/2014/197072A2 |
A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator.
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WO/2014/197219A1 |
A combustor arrangement (10) including: a pilot burner (22) having a pilot cone (62); a plurality of clockwise (130) main swirlers interposed among a plurality of counterclockwise (132) main swirlers and disposed concentrically about the...
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WO/2014/197439A1 |
An example system includes a combustion chamber including at least one inlet and at least one outlet, and at least one reflective surface to direct shock waves in a pattern that meets at a midline nodal point. The example system also inc...
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WO/2014/197045A2 |
A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.
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WO/2014/191495A1 |
An annular combustion chamber is described which has a longitudinal axis, a combustion chamber head end (24) at which at least one burner (107) is arranged, a combustion chamber outlet (6), and a combustion chamber wall. The combustion c...
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WO/2014/187659A1 |
The invention relates to a heat shield tile (10), which can be detachably arranged on a bearing structure of a heat shield (120) by means of at least one retaining element. The heat shield tile has a cold side (1) facing the bearing stru...
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WO/2014/189602A2 |
A fuel injector component (94) comprises a body (100), an elongate void (124) and a plurality of bores (129). The body (100) has a first surface (125) and a second surface (130, 132). The elongate void (124) is enclosed by the body (100)...
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WO/2014/189556A2 |
A heat shield for a combustor of a gas turbine engine includes a first edge with a first set of cantilevered members and a second edge with a second set of cantilevered members.
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WO/2014/186150A1 |
A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an ...
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WO/2014/182507A1 |
A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape. The bloc...
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WO/2014/179328A1 |
A casing for a combustor includes an upstream segment, a downstream segment and a joint. The downstream segment is constructed and arranged to move telescopically with respect to the upstream segment and along a centerline. The joint inc...
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WO/2014/178746A1 |
The invention relates to methods and devices for combusting a gaseous or atomized liquid fuel, and more particularly to gaseous or droplet detonation, and can be used in gas turbine engines operating by continuous detonation combustion. ...
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WO/2014/177371A1 |
The invention relates to a burner lance (60), which can be arranged with a longitudinal axis (23) in a main flow direction inside a burner of a gas turbine. A downstream end of the burner lance (60) forms a burner lance tip (62), which i...
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WO/2014/173568A1 |
The invention relates to a heat shield block (30) for a heat shield (20, 22) of a gas turbine (1), which heat shield block can be detachably fastened to a supporting structure (24) by means of at least one retaining element (26, 28). The...
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WO/2014/174012A1 |
A system and method are provided for altering the natural frequency of a dome plate portion of a premixer assembly of a gas turbine combustor. The plate assembly has a dome plate with a central pilot mixer and a plurality of extension ta...
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WO/2014/173578A1 |
The invention refers to a sequential combustor arrangement (104) comprising a first burner (112), a first combustion chamber (101), a mixer (117) for admixing a dilution gas to the hot gases leaving the first combustion chamber (101) dur...
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WO/2014/173660A1 |
The present invention relates to a combustion system of a flow engine comprising at least one combustion chamber, a shared manifold (18) to feed a flow medium via at least two injectors to the at least one combustion chamber and at least...
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WO/2014/174011A1 |
A novel and improved combustion liner for use in a gas turbine engine is provided in which the premixer assembly is removably fastened to the combustion liner. Apparatus and method for removably securing the premixer assembly to the comb...
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WO/2014/174009A1 |
A novel and improved swirler assembly for use in a combustion liner of a gas turbine engine is disclosed. The swirler assembly is removable and sized to provide an improved assembly, repairability, and fit-up in the combustion liner. The...
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WO/2014/169127A1 |
A heat shield for a combustor of a gas turbine engine includes an outer edge surface with an outlet of an edge cooling passage, the edge cooling passage oriented to direct cooling air generally upstream relative to a combustion gas flow.
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WO/2014/168654A1 |
An igniter tube assembly (100) includes an igniter (110), an igniter tower (138) with a radially extending portion (148), a ferrule (140) with a radially extending portion (176), and a retainer (142) with a radially extending portion (19...
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WO/2014/165084A1 |
A sensor housing (1) is provided. The sensor housing includes an elongated body (2) having an open end (23) and a closed end (22). An opening (21) is disposed axially within the elongated body through the open end and is configured to re...
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WO/2014/164429A1 |
A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effus...
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WO/2014/163669A1 |
A combustor assembly for a gas turbine engine (10) includes a hanger (62) and a combustor liner (52) fixed to the hanger such as, for example, by an annular weld joint (72). The combustor liner has an inner surface (56) extending along a...
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WO/2014/158243A1 |
A diffuser (54) is disclosed that includes a splitter (62) having a blunt forebody useful in re-starting a boundary layer. The blunt forebody can be used to create a static pressure bow wave and interaction with a passing fluid stream th...
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WO/2014/154401A1 |
The invention relates to a combustion system (1) having a combustion chamber (2), comprising an outer shell (3) having a support structure (4), a compressor-side (5) and a turbine-side end (6), and having burners (7) at the compressor-si...
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WO/2014/154931A1 |
The invention relates to a method and apparatus for burning hydrocarbons or other combustible liquids and gases, as well as to the manufacture and use of such an apparatus. An apparatus (APP) has been provided with at least one inlet for...
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WO/2014/160299A1 |
A liner panel for a combustor of a gas turbine engine includes a nominal wall thickness and a thickened wall thickness in the region of a hot spot.
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WO/2014/158252A1 |
An improved fastening system (42) and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system (42) could employ a metallic faste...
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WO/2014/149078A1 |
A material which exhibits auxetic characteristics and control of thermal expansion characteristics while experiencing significant stress reduction is disclosed. The material has a repeating pattern of void structures along both lateral s...
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WO/2014/149190A1 |
A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fu...
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WO/2014/150474A1 |
A combustion system for a gas turbine engine including a combustor assembly comprising a combustor basket having a downstream terminal end, and a transition duct extending downstream from the combustor basket and having an upstream end l...
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WO/2014/147325A1 |
The invention mainly relates to a system (24) for injecting air and fuel for the annular combustion chamber bottom (10) of a turbine engine, comprising at least two devices for injecting fuel, among which are a central injector (26) and ...
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WO/2014/149081A1 |
An improved combustor for a gas turbine is operable to provide high combustion efficiency in a compact combustion chamber. The combustor includes a counter swirl doublet for improved fuel/air mixing. The enhanced combustor assembly and m...
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WO/2014/150437A1 |
An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further ...
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WO/2014/152875A1 |
A gas turbine engine includes an inner annular combustor radially inboard of an outer annular combustor. An outer variable turbine vane array is downstream of the outer annular combustor and an inner variable turbine vane array downstrea...
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WO/2014/149288A1 |
The present techniques are directed to a system and methods for operating a gas turbine system. An exemplary gas turbine system includes an oxidant system, a fuel system, and a control system. A combustor is adapted to receive and combus...
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WO/2014/148166A1 |
This combustor (4) comprises a plurality of fuel nozzles (20) that extend in the axial direction of the combustor body and are capable of injecting fuel from injection holes (24) disposed on the combustion chamber side. The combustor (4)...
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