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Matches 1 - 50 out of 9,052

Document Document Title
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...  
WO/2018/132123A1
The invention is related to a stator vane assembly for a gas turbine engine in which both higher pressure cooling air and lower pressure cooling air are both supplied to the stator vane assembly to cool both an airfoil (20) and inner and...  
WO/2018/131425A1
In order to enhance the efficiency of a gas turbine, this split ring surface-side member is included in a split ring, disposed at a position on the stationary side of the gas turbine and facing a moving blade, and forms a portion of a co...  
WO/2018/129438A1
Various arrangements of a turbine for a rotating coalescer element of a crankcase ventilation system for an internal combustion engine are described. In some arrangements, the turbine is an impulse turbine, which is also known as a pelto...  
WO/2018/128600A1
A gas turbine engine (10) has a side seal (25a) located between adjacent exit pieces. The side seal (25a) comprises a first seal side (23a) and a second seal side (24a) that contact each other. The first seal side (23a) has a spring (26a...  
WO/2018/119763A1
Disclosed is a nozzle partition plate assembly unit body of a steam turbine. A plurality of through holes are integrally formed in the nozzle partition plate assembly unit body, and each of the through holes forms a steam nozzle in commu...  
WO/2018/118217A2
A rotary machine is provided. The rotary machine includes a turbine section with a casing and a ring coupled within the casing. The ring has a groove. The rotary machine also includes a nozzle coupled to the ring. The nozzle has a first ...  
WO/2018/118217A3
A rotary machine is provided. The rotary machine includes a turbine section with a casing and a ring coupled within the casing. The ring has a groove. The rotary machine also includes a nozzle coupled to the ring. The nozzle has a first ...  
WO/2018/110009A1
This split ring and this gas turbine are provided with: a main cooling space (37) that receives cooling air (CA) from the outside and that is provided to the outside of a split ring (27) in a split body (31); a plurality of first cooling...  
WO/2018/110460A1
Provided is a transition duct 30 that forms an annular gas flow channel 40 through which a main flow gas flows from a high-pressure turbine to a low-pressure turbine, wherein the gas flow channel 40 has an inner peripheral flow channel s...  
WO/2018/103910A1
The invention relates to a system for operating an internal combustion engine, which discharges residual heat during operation via an exhaust gas, said residual heat in turn being used in a thermodynamic cycle, in order to vaporize a wor...  
WO/2018/101303A1
This gas turbine high-temperature component is provided with: a body; a porous part through which a cooling gas can pass and which is provided as at least a part of the body or on at least a part of the body; and at least one filter that...  
WO/2018/100278A1
The invention relates to a guide vane (24) for an aircraft bypass turbomachine, the aerodynamic part (34) thereof comprising a first internal lubricant cooling passage (50a) in which heat transfer means are arranged and a second internal...  
WO/2018/099591A1
The invention relates to an exhaust gas guide section for an exhaust gas turbocharger, wherein the exhaust gas guide section (1) is designed for through flow, and wherein a wheel chamber (8) is designed for the rotatable holding of a bla...  
WO/2018/101190A1
A high-temperature component (10) for a gas turbine is provided with a main body part (40) and a porous part (42) through which a cooling gas can pass, and is configured such that, in accordance with one or both distributions of a heat l...  
WO/2018/099619A1
The invention relates to a turbocharger having a turbine, a compressor, and a bearing housing (2), wherein the turbine has a turbine housing (1), a nozzle ring (3), and a turbine rotor. The turbocharger furthermore comprises a fastening ...  
WO/2018/102644A1
A component including a wall (20) with a first surface, a second surface opposite the first surface, and at least one aperture (32) formed within the wall (20) and extending from the first surface to the second surface. At least one boss...  
WO/2018/091871A1
A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extending from a nozzle ring though slots in a shroud, are shaped on one side to as to substantially conform to the profile of the surface of the slot, whereby a ...  
WO/2018/093627A2
An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber is configured to direct cooling air inside of the airfoil. The assembly includes an impingement hole disposed inside the airfoi...  
WO/2018/093627A3
An assembly comprises a cooling chamber (102) disposed inside an airfoil (100) of a turbine assembly. The cooling chamber (102) is configured to direct cooling air inside of the airfoil (100). The assembly includes an impingement hole (1...  
WO/2018/089023A1
An end or intermediate casing for a combustion turbine engines includes prefabricated vanes of a first metal. Ends of the prefabricated vanes are then embedded within cast-in place inner and outer, annular-shaped ring castings, formed fr...  

Matches 1 - 50 out of 9,052