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Patent Searching and Data


Matches 401 - 450 out of 23,225

Document Document Title
WO/2018/218530A1
Provided is a centering and twist lock combination mechanism (10) for a multistage high-speed steam turbine, comprising a rotary shaft (12) and a plurality of stage impellers (16, 18, 20, 22) mounted on said rotary shaft (12); said plura...  
WO/2018/219611A1
In summary, the invention relates to a compressor stator vane (14) for axial compressors (10), comprising a cantilevered airfoil (22) attached to a compressor casing (18) via a blade root, the airfoil (22) comprising an airfoil tip (28) ...  
WO/2018/221596A1
The present invention minimizes wear in a turbine disk and a blade root section of a moving blade when a composite material is used in the moving blade. This composite material blade (1) comprises a blade section (10) and a blade root se...  
WO/2018/222192A1
An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, wh...  
WO/2018/190932A3
A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge span...  
WO/2018/215207A1
The invention relates to a turbine blade (1), in particular a rotor blade or guide vane, comprising a blade body (3) which is at least substantially radially penetrated by a cooling channel (12), and a sheet metal insert (15) which is in...  
WO/2018/215143A1
An aerofoil (200) for turbo machinery. The aerofoil comprises a first wall (202) having an outer surface (206) and an inner surface (208), and a second wall (204) having an outer surface (210) and an inner surface (212). The first wall a...  
WO/2018/215718A1
In order to limit the air flow required to cool its blade member, a blade (30) for an aircraft turbomachine turbine comprises, in its blade member (34), a main passage (50) configured to collect a main air flow (F1) from an air inlet and...  
WO/2018/215323A1
The invention relates to a method for producing a vibration-damping structure combination (18) for damping vibrations for movable masses (10), said structure combination having a first structure (2) and a further structure (3), the furth...  
WO/2018/215370A2
A gas turbine engine rotor disc is presented. The rotor disc includes a hub, a web, a blade retention arrangement, a rotational axis, a first axial side and a second axial side. The hub has a central bore around the rotational axis. The ...  
WO/2018/217213A1
System (10) and methods (1000) for structural braze repair of high gamma prime nickel base gas turbine components (1). The system may include a controller (200) operably connected to a heating system (100), e.g., a vacuum furnace, for co...  
WO/2018/215519A1
The invention relates to a method for producing a turbine blade (1), wherein the turbine blade (1) is manufactured by means of an additive manufacturing technique, wherein the turbine blade (1) is formed section-by-section comprising a c...  
WO/2018/215712A1
The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage (50...  
WO/2018/211222A1
The invention relates to a method for regulating the internal temperature of the vanes of an impeller comprising a circuit for supplying cooling gas and a plurality of vanes (100) each comprising a pressure-side wall (108) and a suction-...  
WO/2018/209374A1
The invention relates to a method for improving the wear resistance of a highly loaded component provided with a corrosion protection layer, according to which a chemical nickel layer is deposited on the component as a corrosion protecti...  
WO/2018/206860A1
Translational flight is provided by a propeller or rotor. There are single propellers or rotors and contra-rotating double propellers or rotors. The first propeller or rotor evacuates the depression in front of the propeller or rotor for...  
WO/2018/206306A1
The invention relates to a method for maintaining an axial-flow turbomachine (1), which has a support structure (2) and a plurality of axially adjacent guide vane rings (3, 4, 5) each of which has a plurality of guide vanes (6), each gui...  
WO/2018/207702A1
Provided are a composite material blade and a method for manufacturing the composite material blade such that the degree of contour and precision of thickness can be sufficiently ensured, and the manufacturing cost can be reduced. The co...  
WO/2018/208577A1
An axial compressor (12) of a turbine engine (10) includes a plurality of disk and spacer pairs (14) oriented along a common axis of rotation. Each of a disk (16) and a spacer (18) of the disk and spacer pairs (14) has a contacting face ...  
WO/2018/202738A1
These new thrusters simultaneously use wheels of the CARPYZ THRA "Turbo Powered Helicopter Reactor" type and wheels of the CARPYZ TaG ''Bucket Turbines'' type or wheels of the CARPYZ TaC ''Scoop Turbines" type, representing real global t...  
WO/2018/198932A1
A shaft 13 for turbo chargers comprises a low-strength section 25 set to a breaking strength at which same breaks when a preset prescribed load is applied, said section being in an area between a compressor-side bearing 15 and a compress...  
WO/2018/197800A1
The invention relates to a sealing device for use between a rotor part and a stator part, comprising at least one abradable coating (46) interacting with at least two upstream and downstream rubbing strips. Axially upstream of the rubbin...  
WO/2018/199237A1
The thermal barrier coating is provided with a ceramic layer (120) formed on a heat-resistant alloy substrate and containing ceramic substance. The ceramic layer (120) has: a first dense layer (121); an intermediate porous layer (122) la...  
WO/2018/197856A1
The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid...  
WO/2018/197114A1
The invention relates to a ceramic sealing system between a rotor blade (120) and a housing (1''). By means of the combination of a small porous zirconium oxide layer (11) on a turbine rotor blade, which zirconium oxide layer faces a cer...  
WO/2018/196957A1
The invention relates to a turbine blade (1), particularly a moving blade or a fixed blade, comprising at least one blade platform (3) and a blade (4) connected thereto, said blade (4) comprising a leading edge (5) and a trailing edge (6...  
WO/2018/195778A1
A gas turbine component includes a substrate and a corrosion resistant layer coupled to the substrate. The corrosion resistant layer includes zirconium silicate and is configured to protect the substrate from exposure to a vanadium corro...  
WO/2018/196956A1
The invention relates to a turbine blade (1), particularly a moving blade or a fixed blade, comprising a blade root (2), a platform (3) connected thereto, and a blade (4) connected to the side of the platform (3) that faces away from the...  
WO/2018/193155A1
The invention deals with cross-flow turbines meant to be immersed in undisturbed free fluid flow fields such as wind, tidal, river or shallow ocean wave flow, crossing perpendicularly the rotation axes of the turbine. The curved blades o...  
WO/2018/189432A1
The invention relates to a turbine blade comprising a blade root and a blade (13) extending radially outwards from the blade root (12), said blade (13) comprising a first inner cooling circuit comprising a lower surface cavity (33, 36) e...  
WO/2018/189380A1
A component (1) for a turbomachine, which is provided with a protective coating (24) at least in a subregion (22) of its surface (20), is intended to be comparatively easy and thus cost-effective to produce and yet exhibit a particularly...  
WO/2018/189434A2
The invention relates to an aviation turbine blade (10), characterised in that it comprises at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second throu...  
WO/2018/190932A2
A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge span...  
WO/2018/189433A2
The invention relates to an aviation turbine blade (10) extending radially from a blade root (14) as far as an upper partition wall (26), said blade (10) comprising a plurality of inner cavities (C1-C10) defining at least one cooling cir...  
WO/2018/186921A2
A component for a turbine engine comprises a wall with a surface along which a hot airflow passes, a second surface along which a cooling airflow passes, and an insert mounted to the wall wherein the material used for the insert can have...  
WO/2018/184788A1
The invention relates to a method for sealing an annular gap (11) in a turbine with a housing (1) and a rotor (2), which is arranged in the housing (1), is mounted to rotate about its central longitudinal axis, and is equipped with a plu...  
WO/2018/186891A1
A cooling assembly comprises a cooling cavity disposed inside of a turbine assembly. The cooling cavity is configured to direct cooling air inside a body of the turbine assembly. The cooling assembly comprises a cross-bank fluidly couple...  
WO/2018/185445A1
The invention relates to a diffuser (5) of a radial or hybrid compressor (2) comprising an internal shroud (20), an external shroud (30) and a series of vanes (10), the trailing edge (12) of each vane (10) being curved in such a way that...  
WO/2018/184782A1
The use of MAX phases creates a large aluminum or chromium reservoir for forming oxidation-inhibiting layers.  
WO/2018/180781A1
Provided is a gas turbine (A) using a denitration catalyst and ammonia as a reducing agent for the denitration of combustion gas, wherein the ammonia is supplied, along with cooling air supplied from a compressor (1), to turbine vanes (3...  
WO/2018/182816A1
A cooling circuit for a trailing edge region of a turbine airfoil where the trailing edge is relatively thin, the cooling circuit having a series of aftward-flowing channels alternating with a series of forward-flowing cooling channels, ...  
WO/2018/177864A1
The invention relates to a turbocharger (1) for an internal combustion engine, comprising - a bearing housing (41), in which a rotor shaft (14) is mounted rotatably about a rotor axis of rotation (15); - an exhaust gas turbine (20) havin...  
WO/2018/181559A1
The present invention addresses the problem of providing a thermal barrier coating film (13) which exhibits high durability even in a gas turbine used in a molten salt environment such as a heavy oil fired gas turbine, and which can be f...  
WO/2018/178603A1
The invention concerns a turbine component, such as a turbine blade or a distributor fin, for example, comprising a substrate made from single-crystal nickel superalloy, and a metal sublayer covering the substrate, characterised in that ...  
WO/2018/175003A1
A system is disclosed including a first blade (102), a second blade (104), and a snubber (100) disposed between a pressure side (106) of the first blade (102) and a suction side (108) of the second blade (104). An inclination angle of a ...  
WO/2018/175356A1
The invention is related to a bladed rotor system (10) for a turbomachine including blades (14) mounted circumferentially on a rotor disc (12), and a plurality of under-platform dampers (30). Each damper (30) is located between adjacent ...  
WO/2018/167384A1
The present invention relates to a method for obtaining a solid blade of a turbomachine, comprising a core, a tip and a root, the method comprising: - a step of producing a blank from at least two parts (50, 51), at least one of which is...  
WO/2018/169668A1
A bladed rotor system (10) for a turbomachine includes a row of blades (14) mounted on a rotor disc (12). Each blade (14) includes an airfoil (16) with a mid-span snubber (30). The row of blades (14) includes first (H) and second (L) set...  
WO/2018/169665A1
A bladed rotor system (10) includes a circumferential row of blades (14) mounted on a rotor disc (12). Each blade (14) includes an airfoil (16) and a shroud (30) attached to the airfoil (16) at a span-wise height of the airfoil (16). The...  
WO/2018/167632A1
The present invention relates to a method for constructing bladed rings for radial turbomachines. The method comprises: preparing a cylindrical block (M; M1, M2); making in the cylindrical block (M; M1, M2) a wavy circumferential cut (28...  

Matches 401 - 450 out of 23,225