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WO/2016/168425A1 |
A gaseous fuel introducer comprising a first mounting surface shaped and located to couple to a first wall of a charger; a first input, the first input being an air input; a second input, the second input being a gaseous fuel input; and ...
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WO/2016/162105A1 |
The invention relates to a controller for an exhaust gas conductive portion, through which a flow can pass, of a turbocharger. The controller (13) is designed to open and close a bypass channel (11) in the exhaust gas conductive portion ...
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WO/2016/162249A1 |
A blade (51) and an assembly tool (87) for assembling a blade set to a rotor disc (35) is disclosed. The blade (51) comprises a root portion (50), an aerofoil (54) and a shroud (56), the root portion (50) has two lateral sides each defin...
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WO/2016/164332A1 |
An integrated fan heat exchanger stator assembly is provided including a hub and a casing. A plurality of elements is arranged between the hub and the casing. The plurality of elements is separated from one another by a plurality of exte...
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WO/2016/162106A1 |
The invention relates to a regulating device for an exhaust-gas-conducting section of an exhaust-gas turbocharger, wherein the regulating device (19) is designed for guiding a flow of a fluid into a bypass duct (22), which is formed in t...
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WO/2016/164661A1 |
The invention relates to an exhaust gas supply arrangement (1) to a turbine wheel (11) of an exhaust gas turbocharger (2), having a flange (14) for connecting to a manifold (3) of an 5 internal combustion engine (4), an exhaust gas suppl...
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WO/2016/156200A1 |
The present invention relates to a vane device (100) for a gas turbine. The vane device (100) comprises: an inner shroud (110) and an outer shroud (120), an aerofoil (101, 115) arranged between the inner shroud (110) and the outer shroud...
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WO/2016/156211A1 |
The invention relates to a guide vane assembly (1) comprising at least partially resilient brackets (25; 31; 34), each of which has some tolerance between a web (7) of a guide vane (4) and an inner ring (3) of the guide vane assembly (1)...
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WO/2016/156744A1 |
The invention relates to an oil jet (10) for a turbine engine, comprising a body (16) including a circulation pipe (18) intended for the flow of a pressurised fluid. The body (16) of the jet (10) comprises a first portion (24) and a seco...
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WO/2016/156743A1 |
The invention relates to a turbine engine which comprises at least one stator bladed sector (10) and a fluid distribution circuit (22), the stator bladed sector comprising at least one blade (12), a fluid intake (25a), a fluid outlet (25...
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WO/2016/157127A1 |
The invention refers to a sandwich arrangement comprising at least two peripheral disposed ceramic panels (101a, 101b) and a ceramic felt (110) which is inserted be- tween a first and second ceramic panel, The material of the first ceram...
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WO/2016/155923A1 |
The present invention relates to a transition duct assembly (1) comprising a plurality of transition ducts (2), each transition duct (2) having a tubular main body (3) and a flange portion (4) provided at a downstream end of said tubular...
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WO/2016/158533A1 |
A support device is provided with: a support member having a body disposed in a recess provided in the upper surface of the lower half of an outer member, the support member further having a protrusion provided on the body, the protrusio...
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WO/2016/152573A1 |
A blade having a flow path forming plate (60o) that defines a portion of a combustion gas flow path. Multiple rear passages (75) opening at a rear end surface (62b) are formed in the flow path forming plate (60o). The opening density of ...
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WO/2016/148692A1 |
A stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection, provide mechanical dampening and prevent clearance loss relative to adjacent blade rotor disks i...
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WO/2016/142631A1 |
The invention relates to an element of a stator guide of an axial compressor of a turbomachine, in the form of a monobloc assembly, the outer shape thereof being a cylinder sector forming, in a radially outer manner, an outer shroud sect...
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WO/2016/139574A1 |
Expansion turbine (100) for a working fluid in an organic Rankine cycle, comprising a housing (21), at least one inlet duct (10) for working fluid feeding and an outlet duct (20) for working fluid discharge, at least one statoric group (...
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WO/2016/134907A2 |
The invention relates to a stator or rotor blade device (1) which is cast from a metal alloy and comprises at least one blade base (3) and an airfoil (4) designed as one piece with the blade base (3), a hollow space (6) extending from th...
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WO/2016/133486A1 |
A ring segment system (100) for a gas turbine engine (10) is disclosed. The ring segment system (100) may be formed from ring segments (50) that circumferentially surround a rotor assembly (40). The ring segments (50) may each include a ...
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WO/2016/129949A1 |
The present invention relates to an axial flow turbine, comprising: a rotor mounting part; a housing having a fluid supply part surrounding the rotor mounting part; a rotor which is installed at a rotation shaft installed in the housing ...
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WO/2016/129375A1 |
This gas turbine component comprises a metal intermediate structure (110) and a ceramic layer (130). A gas path surface (102) which faces toward a combustion gas flow path (GP) side in a radial direction (Dr), and a pair of side surfaces...
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WO/2016/127241A1 |
A two-way flow control device including: a housing defining a first opening interface and a second opening interface, a rotor having a plurality of blades, each blade controllable to be angled in a range of positive and negative blade an...
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WO/2016/128665A1 |
The invention relates to a turbine engine assembly comprising an air flow guide assembly, including at least one guide vane (21) and at least one structural arm (30), said vane and arm extending radially about an axis (X-X). The arm incl...
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WO/2016/129588A1 |
Provided is a coated member which is provided with a heat shielding coating layer that exhibits excellent characteristics in a high temperature environment in which water vapor is present. A coated member (100) which is provided with a h...
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WO/2016/128664A1 |
The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line...
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WO/2016/124853A1 |
The invention relates to a plug (50) for preventing corrosion of an attachment opening (22). Said plug comprises: - a bottom surface (51) including an opening (60) for receiving a head (27) of a tightening means (23); - a top surface (52...
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WO/2016/121163A1 |
A turbine blade provided along the radial direction of a turbine is provided with an airfoil part positioned inside a fluid channel of the turbine, and a shroud part positioned on the inner side or outer side of the airfoil part in the r...
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WO/2016/121684A1 |
A cooling system (60) is provided with a high-pressure bleed line (61) for bleeding high-pressure compressed air (A1) from a first bleed position (Pb1) of a compressor (10) and sending the air to a first high-temperature component (44a),...
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WO/2016/118129A1 |
A transition duct system (100) for routing a gas flow from a combustor (102) to the first stage (104) of a turbine section (106) in a combustion turbine engine (108), characterized in that the transition duct system (100) includes one or...
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WO/2016/111249A1 |
Provided are an austenite-based heat-resistant steel and a turbine component, which have a reduced linear expansion coefficient while maintaining high-temperature creep strength, and with which satisfactory weldability can be ensured. Th...
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WO/2016/111773A1 |
A metal insert tube (460) of a turbine vane (452) is disclosed. The insert tube (460) includes a pressure side wall (461), a suction side wall (464) opposite and spaced apart from the pressure side wall (461), a leading edge (462), and a...
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WO/2016/103340A1 |
A nozzle structure (3) is provided between a rotor (2) which rotates about an axis (O) and a casing (1) which surrounds the rotor (2) from the outer peripheral side. The nozzle structure (3) comprises: an outer ring (20) which is dispose...
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WO/2016/102128A1 |
The invention relates to a radial compressor for a turbocharger, in particular of an internal combustion engine, and to a turbocharger comprising such a radial compressor. The invention further relates to a method for operating such a ra...
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WO/2016/093829A1 |
A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a tra...
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WO/2016/094035A1 |
A connection system (10) for a combustor assembly (12) of a turbine engine (14) whereby the connection system (10) includes a transition cylinder (18) with a transition cylinder cooling system (16) is disclosed. The connection system (10...
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WO/2016/089970A1 |
A vane (110) for an Inlet Guide Vane (IGV) (112) of a multistage compressor (100) includes a root portion (114), a tip portion (116), and an airfoil (118) extending therebetween. The vane (110) is configured such that a ratio of the maxi...
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WO/2016/088833A1 |
A sprayed-coating formation method equipped with: a step for preparing a spray target member having a surface in which one end of a plurality of holes opens; a step for preparing a plurality of masking pins comprising a metal; an inserti...
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WO/2016/080957A1 |
A transition duct exit frame (10) for supporting a transition duct (12) extending downstream from a combustor (14) to a turbine assembly (16) in a gas turbine engine (18) and including one or more transition duct exit frame inserts (20) ...
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WO/2016/079223A1 |
The invention relates to a thermal energy machine (1), in particular a gas turbine (2), comprising a compressor (3) for compressing an air mass flow (5) flowing along the machine longitudinal central axis (6) in an axial flow direction (...
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WO/2016/079221A1 |
The invention relates to a diffuser (1) of a thermal energy machine (3), in particular of a gas turbine (5), comprising a diffuser inlet (20), a diffuser outlet (22), and a plurality of air-guiding elements (23), wherein an air mass flow...
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WO/2016/079523A1 |
In an effort to increase the reliability and net power and efficiency benefit of the axial-and mixed-flow turbocharger turbine, there is provided, a tapered, axially translatable ("sliding nozzle") flow restrictor member (197) to provide...
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WO/2016/080025A1 |
An axial-flow-machine blade according to the present invention is provided with: a blade body (39) that extends in a radial direction; a platform (end wall)(41) that is provided at an end section (40) of the blade body (39) in the radial...
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WO/2016/078984A1 |
The invention relates to a steam turbine having an inflow ring channel (3) which is connected to an inflow connecting piece (9) in terms of flow technology, wherein the inflow connecting piece (9) is designed in such a way that an incomi...
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WO/2016/071224A1 |
A sector (2) for the assembly of a stage (1) of a turbine comprises a central (2a) and a peripheral portion (2b); a plurality of blades (6) attached between the central (2b) and the peripheral portions (2a); a first (16) and a second sid...
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WO/2016/068857A1 |
A seal assembly (12) between a transition seal structure (14) associated with a downstream end (16) of a transition duct (10) and a vane seal structure (18) associated with an upstream end (20) of a vane structure (22) in a first row van...
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WO/2016/068859A1 |
An airfoil attachment system (10) for a modular turbine vane (12) of a gas turbine engine (14) including an outer attachment system (10) with forward and aft radially extending axial hooks (20, 22) configured to be coupled directly to a ...
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WO/2016/069599A1 |
An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels ...
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WO/2016/059300A1 |
A stator mechanism for a turbine, the stator mechanism comprising a cylindrical housing which has a longitudinal center axis, wherein the cylindrical housing comprises a plurality of holes in an outer periphery of the cylindrical housing...
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WO/2016/057112A1 |
A centrifugal compressor diffuser (42) includes a plurality of diffuser flow passages (22) extending through an annular diffuser housing (20) and circumferentially bounded by diffuser vanes (23) and axially bounded by forward and aft wal...
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WO/2016/056580A1 |
Provided is a turbine stator blade cooling structure that can suppress the use of compressed air. Also provided is a gas turbine engine that is provided with the turbine stator blade cooling structure. A turbine blade cooling structure t...
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