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公开(公告)号：US20240360816A1
公开(公告)日：2024-10-31
申请号：US18766314
申请日：2024-07-08
申请人： James D. Rudd
发明人： James D. Rudd
CPC分类号： F03G3/06 , F01D15/10 , F03B17/025 , F03B17/04 , F03B17/06 , F05D2220/76
摘要： An engine system includes three communicating fluid vessels that each contain a fluid. A first interconnecting fluid conduit containing the fluid rotatably couples the second fluid vessel to the first fluid vessel and acts as a lever. A second interconnecting fluid conduit containing the fluid rotatably couples the third fluid vessel to the first fluid vessel and acts as another lever. By increasing the fluid column heights in the communicating fluid vessels, torque is applied to the levers to cause the second and third fluid vessels to revolve around the first fluid vessel.
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公开(公告)号：US20240360771A1
公开(公告)日：2024-10-31
申请号：US18308968
申请日：2023-04-28
发明人： Michael G. McCaffrey
CPC分类号： F01D11/14 , F02C7/28 , F05D2240/55
摘要： A blade outer airseal (BOAS) assembly of a gas turbine engine includes a plurality of BOAS segments arrayed circumferentially about the engine central longitudinal axis, and a plurality of BOAS carriers located radially outboard of the plurality of BOAS segments. Each BOAS carrier is supportive of at least one BOAS segment. The BOAS assembly includes plurality of adjustment levers. Each adjustment lever is operably connected to at least two BOAS carriers of the plurality of BOAS carriers. Rotation of each adjustment lever about a respective pivot axis urges movement of the plurality of BOAS segments in a radial direction thereby adjusting a radial gap between the turbine rotor and the plurality of BOAS segments.
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公开(公告)号：US20240360769A1
公开(公告)日：2024-10-31
申请号：US18688009
申请日：2022-08-16
发明人： Nicolas Daniel DELAPORTE , Pierre Marie MULHEIM , Arnaud MARTINE , Antoine GIGUET , Vincent GOYON
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D5/3023 , F05D2220/323 , F05D2240/20 , F05D2240/30
摘要： A foil for a turbomachine rotor blade, configured to be mounted on a root of the rotor blade and including an embossment located in a lower surface of the foil and forming, in the lower surface of the foil, a convex protrusion capable of being inserted into a housing formed in a lower face of the blade root.
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公开(公告)号：US20240360768A1
公开(公告)日：2024-10-31
申请号：US18764770
申请日：2024-07-05
CPC分类号： F01D5/282 , F01D9/02 , F01D25/005 , F05D2220/323 , F05D2240/12 , F05D2240/30 , F05D2300/603
摘要： A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion. The leading edge protector includes at least one projection extended past a base of the airfoil to a root of the airfoil.
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公开(公告)号：US20240360765A1
公开(公告)日：2024-10-31
申请号：US18408342
申请日：2024-01-09
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F05D2230/21
摘要： A method for manufacturing a blade for a gas turbine includes forming a blade body including an airfoil, forming a groove adjacent to a trailing edge of the airfoil in an outer surface of the airfoil, positioning a cover on the blade body such that it covers the groove and such that an outer surface of the cover forms a continuous surface with the outer surface of the airfoil, and joining the cover to the airfoil so that the cover and the groove define a cooling channel.
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6.发明公开公开(公告)号：US20240359256A1
公开(公告)日：2024-10-31
申请号：US18640177
申请日：2024-04-19
申请人： SAFRAN AERO BOOSTERS
IPC分类号： B23K20/12 , B23K101/00 , F01D5/02
CPC分类号： B23K20/129 , F01D5/02 , B23K2101/001 , F05D2230/239
摘要： A method for sizing a section of a junction by orbital friction welding with an eccentric e, between a blade and a stub of a bladed disk for a turbomachine. The sized section has a rounded contour at one or two ends of said section along a chord of the blades, each corresponding to a leading edge or a trailing edge of said blades, said rounded contour(s) having over a sector of at least 120° an average radius of at least twice the eccentric e.
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公开(公告)号：US12129796B1
公开(公告)日：2024-10-29
申请号：US18138366
申请日：2023-04-24
CPC分类号： F02C7/057 , F01D25/08 , F05D2240/127
摘要： A vortex restart structure including a flow passage having a first wall and a second wall opposite the first wall, each of the first wall and the second wall including a parting surface; multiple flow turbulators extending from at least one parting surface of the first wall or the second wall; and at least one vortex restart structure extending from at least one parting surface of the first wall or the second wall, wherein the at least one vortex restart structure extends from the parting surface into the flow passage beyond the multiple flow turbulators.
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公开(公告)号：US12129770B1
公开(公告)日：2024-10-29
申请号：US18497526
申请日：2023-10-30
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F05D2220/3218 , F05D2250/74
摘要： A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of TABLE I and TABLE II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US12129765B2
公开(公告)日：2024-10-29
申请号：US18388567
申请日：2023-11-10
发明人： Krzysztof Andrzej Woszczak , William Patrick Rusch , Samuel Nathan Merrill , Ejiro Anthony Oruaga , David John Nelmes , Justyna Ludwika Wojdyło , John Francis Nolan
CPC分类号： F01D25/243 , F01D21/003 , F01D25/02 , F01D25/28 , F05D2230/644 , F05D2240/14 , F05D2250/11 , F05D2260/30
摘要： A method and system for aligning a component within a turbine casing, and a related turbine casing, are disclosed. In a top-on position, a location of a reference point and another, vertically spaced reference point on the lower casing are measured. After removing at least the upper casing, the reference points' locations are measured again, and the locations of a reference point on an upper surface of the HJ flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a HJ flange surface distortion adjustment. The component support position is adjusted by the prediction offset value to improve alignment.
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10.发明公开公开(公告)号：US20240353343A1
公开(公告)日：2024-10-24
申请号：US18303965
申请日：2023-04-20
CPC分类号： G01N21/8422 , F01D5/288 , F05D2230/10 , F05D2230/90 , G01N2021/8433
摘要： The present application provides a cooling hole location system for locating a cooling hole in a gas turbine component, wherein the cooling hole is covered by a thermal barrier coating. The cooling hole location system may include a light source positioned on a first side of the gas turbine component and an optical detector positioned on a second side of the gas turbine component. The optical detector detects light from the light source visible through the thermal barrier coating covering the cooling hole.
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