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Matches 1 - 50 out of 9,155

Document Document Title
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/2018/217485A1
A refractory ceramic component (10) for a gas turbine engine (100) is employed that is more cost effective than typical components used in the gas turbine engine (100). The refractory ceramic component (10) may include a refractory ceram...  
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/2018/210957A1
Method for creating at least one aircraft turbomachine vane using additive manufacturing, the method comprising a step of additive manufacturing of said vane on beds of powder using selective laser melting, the manufacturing being perfor...  
WO/2018/211270A1
An outlet guide vane for a turbofan engine, which results in reduced noise. The outlet guide vane may comprise an aerofoil, the aerofoil comprising at least porous section, wherein the at least one channel or porous section is positioned...  
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/2018/202441A1
The present invention discloses an inlet guide vane assembly of a gas turbine and a gas turbine which comprises an inner inlet casing and an outer inlet casing. The inlet guide vane assembly comprises: a plurality of inlet guide vanes, e...  
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/2018/196957A1
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/2018/196198A1
Disclosed is an impeller tube-type nozzle (101) for a gas turbine, comprising an inlet section (108), a retraction section (107) and an outlet section (106). The inlet section (108) is a section of annular channel, the retraction section...  
WO/2018/188776A1
The invention relates to an adjusting device (100, 200, 300, 400) having: a valve shaft (101; 201; 301; 401) with a valve head (103; 203; 303; 402) at a first end, said valve head being designed to open and close the flow opening, and a ...  
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/2018/186921A3
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/2018/180781A1
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/2018/183078A1
A system effective for dual utilization of cooling fluid in a gas turbine engine is provided. A cooling annulus (22, 70) is subject to a hot-temperature combustion flow received from a combustor basket and may include a liner (72) includ...  
WO/2018/172715A1
The invention relates to a turbomachine assembly comprising: - a casing comprising: - an internal hub (10), - an external ferrule (20) extending around and at a distance from the internal hub (10), - a hollow arm (30), provided with a lo...  
WO/2018/175678A1
The present invention is related to the housing (60) of an exhaust turbine (32) of a turbocharger comprising a first volute (61) and a second volute (62), each of the volutes (61,62) ending in respective first and second guide tongues (6...  
WO/2018/172654A1
A turbine ring assembly comprising ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10) having, in a plane of section defined by an axial direction (DA) and a radial direction (DR) of the r...  
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/2018/164149A1
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/2018/162485A1
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/2018/163877A1
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/2018/164150A1
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/2018/164148A1
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/2018/158544A1
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/2018/154724A1
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/2018/155640A1
An axial flow rotating machine (100) comprises a rotating shaft (1), a rotor blade (4), a casing (2), and a stator blade (7). A stator blade body (70A) comprises: a stator blade first shape part (73A) in which a stator blade intermediate...  
WO/2018/155652A1
In an axial flow rotary machine according to the present invention, a structure comprises a casing-side fin (42). An upstream-side inclined surface (45) that is inclined from the upstream side toward the downstream side is provided to a ...  
WO/2018/156322A1
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/2018/156293A1
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/2018/156316A1
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/2018/155636A1
In an axial flow rotary machine according to the present invention, a moving blade (4) comprises a moving blade shroud (41) and a shroud-side fin (44), and a small gap is formed between said shroud-side fin (44) and a casing (2). The cas...  
WO/2018/151784A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and an upstream end and a downstream end along the longitudinal dire...  
WO/2018/151251A1
A steam turbine is provided with: a rotating shaft (1); a moving blade (4) including a platform (43) and a moving blade main body (40); a casing (2); a stationary blade (7) including a stationary blade main body (70) and a stationary bla...  
WO/2018/146946A1
Provided is a geothermal turbine equipped with a rotor, a casing for housing the rotor, a plurality of moving blades disposed around the rotor, a plurality of stationary blades supported on the casing, and at least one seal part provided...  
WO/2018/146405A1
The invention relates to a turbofan (1) comprising a low-pressure compressor (3); a series of housings (9, 10) arranged downstream of said low-pressure compressor (3) for defining a primary stream, and comprising an upstream edge (19) de...  
WO/2018/147162A1
A blade (12) of an axial flow machine is provided with: an airfoil part (13) having a dorsal surface (13a) and a ventral surface (13b); an end wall serving as a shroud (15) or a platform (14); and a fillet (16) provided along a connectin...  
WO/2018/147875A1
There is provided a component (10) having a plurality of laminates (12) formed from a ceramic matrix composite material stacked on one another to form a stacked laminate structure (14). A seal (28) formed from a resolidifiable ductile an...  
WO/2018/147013A1
Disclosed is a steam turbine which is equipped with a rotor, a casing for housing the rotor, a plurality of moving blades disposed around the rotor, and a plurality of stationary blades supported on the casing, and in which: the stationa...  
WO/2018/144513A1
The invention relates to a housing assembly comprising a housing that has at least one first connection opening and one second connection opening, a first connecting piece with a first flange and a second connecting piece with a second f...  
WO/2018/141504A1
The invention relates to a turbine blade (10) or turbine vane (20) for a gas turbine, comprising successively along a radial direction of said gas turbine, a root (12) for attaching the turbine blade (10) or turbine vane (20) to a carrie...  
WO/2018/141574A1
The invention relates to a non-metal turbine component, particularly a gas turbine component, for example for stationary gas turbines, consisting of ceramic matrix composite (CMC) materials. A CMC turbine component comprising fine and co...  
WO/2018/140139A1
The present disclosure is directed to a gas turbine engine defining an axial centerline, a longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes one or more frames in which the frame...  
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...  
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...  
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 ...  
WO/2018/135283A1
In the present invention, a structure for cooling a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a...  
WO/2018/135212A1
This steam turbine (10) is provided with: a rotor (12); a casing (20) for rotatably housing the rotor (12); and a first stage (40) including a first-stage stator blade (42) fixed to an inner wall part (22) of the casing (20) and a first-...  
WO/2018/134367A1
The invention concerns a transition duct for a multi-stage compressor of a gas turbine engine. Regions of the inner surface of the duct are provided with a predetermined and dissimilar surface roughness to optimise gas flow efficiency wi...  

Matches 1 - 50 out of 9,155