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Matches 51 - 100 out of 22,443

Document Document Title
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/2018/189434A3
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/2018/189433A2
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/2018/190932A3
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/2018/189433A3
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/2018/185070A3
The invention relates to a turbine blade (12, 30) for a gas turbine, comprising a wall, which can be exposed to a corrosive hot gas during intended use of the turbine blade, is partially made from a cast material and is designed as a bla...  
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/2018/186921A3
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/2018/185445A1
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...  
WO/2018/164149A1
This cooling structure for a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) that is curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a second blade w...  
WO/2018/164693A1
Processes are described herein which 3D print a ceramic fiber composite (24, 48) in a printed pattern (308) on a ceramic matrix composite (CMC) component (300) in order to define a plurality of channels (312) between adjacently deposited...  
WO/2018/162485A1
A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turb...  
WO/2018/164791A1
A rotor assembly is provided. The rotor assembly includes a plurality of blades spaced circumferentially. An airfoil of each blade includes a pressure side, a suction side, a pressure side nub extending from the pressure side, and a suct...  
WO/2018/163877A1
A first turbulator 41R which is at least one of a plurality of turbulators comprises: a first section 411 which has a constant projection height from an inner surface 40S; and a second section 412 which is connected at one end to the fir...  
WO/2018/164598A1
The present invention provides a supply system (7) for gas turbine component cooling, wherein the gas turbine component is a hollow component (1) that is required to be cooled, for example a gas turbine blade, a gas turbine vane, a gas t...  
WO/2018/164150A1
This cooling structure for a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) that is curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a second blade w...  
WO/2018/162695A2
The invention relates to a fastener for rotating blades (1) which is suitable for steam turbines, gas turbines or compressors, the base geometry being optimally configured.  
WO/2018/164148A1
This cooling structure for a turbine blade (1) is provided with a lattice structure (23) formed by a first rib pair (33A) and a second rib pair (33B) which are disposed in a cooling passage (17) and overlap each other in a lattice shape,...  
WO/2018/157958A1
The invention relates to a turbine stage, comprising at least one turbine rotor (1) and a plurality of turbine blades (2) arranged over the circumference of the turbine rotor (1), and comprising at least one coupling element (3), bores (...  
WO/2018/158544A1
The invention relates to a blade (100) comprising: a vane body (110) made of composite material having a fibrous reinforcement (120) exhibiting a three-dimensional weave and densified by a matrix, the reinforcement comprising a first par...  
WO/2018/158522A1
A fibrous preform for a turbomachine vane, comprising a main fibrous structure (40) obtained by one-piece three-dimensional weaving, said first main structure (40) comprising a first longitudinal section (41), suitable for forming a vane...  
WO/2018/159686A1
In a rotating machine (1) a tip shroud (51A) of a moving blade (50) includes: a plurality of shroud outer peripheral surfaces (53A, 53B, 53C) provided in such a way that the radial direction positions thereof are positioned further towar...  
WO/2018/154724A1
Provided is a method for measuring a pre-twist amount of a blade, the method including: a spreading dimension acquiring step; a misalignment acquiring step; a correcting step; and a pre-twist amount acquiring step. In the spreading dimen...  
WO/2018/156270A1
Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the l...  

Matches 51 - 100 out of 22,443