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公开(公告)号：US20240308015A1
公开(公告)日：2024-09-19
申请号：US18185867
申请日：2023-03-17
发明人： Zhigang Wang , Andrzej E. Kuczek , Robin H. Fernandez , John D. Riehl , Alan C. Barron , Ahmed Abdillahi Abdi , Jason Nelson , Andrew Joseph Lazur
CPC分类号： B24B1/04 , B24B57/02 , B25J9/0084 , B25J9/0096 , B25J9/026 , B25J9/161 , B25J11/0065
摘要： An ultrasonic impact grinding assembly includes a base with a mount for connecting a workpiece to the base and a first tool arm. The ultrasonic impact grinding assembly also includes a second tool arm. The first tool arm and the second tool arm each include a base end, a distal end, at least one joint between the base end and the distal end, and at least one actuator configured to move the at least one joint. A first ultrasonic impact grinding tool head is connected to the distal end of the first tool arm. A second ultrasonic impact grinding tool head is connected to the distal end of the second tool arm.
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12.发明公开公开(公告)号：US20240301808A1
公开(公告)日：2024-09-12
申请号：US18117919
申请日：2023-03-06
发明人： Jon E. Sobanski
IPC分类号： F01K23/10
摘要： A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, an engine housing, an evaporator, a condenser and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The engine housing includes a cavity radially outboard of and axially overlapping the fan section and/or the bypass flowpath. The evaporator module is within the cavity. The condenser module is within the cavity. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.
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公开(公告)号：US20240301805A1
公开(公告)日：2024-09-12
申请号：US18181149
申请日：2023-03-09
发明人： Paul M. Lutjen , Dairus D. McDowell
CPC分类号： F01D25/243 , F01D9/023 , F05D2240/40 , F05D2260/36
摘要： A component of a gas turbine engine includes a continuous hoop portion extending at least partially around an engine central longitudinal axis of the gas turbine engine and a bolting feature extending from the hoop portion, configured for securing the component to an adjacent component. The bolting feature includes a circumferential arm extending radially and circumferentially from the hoop portion. The circumferential arm defines a radial gap between the circumferential arm and the hoop portion. The circumferential arm includes a bolt opening for installation of a bolt therethrough. A connecting leg extends radially from the hoop portion across the radial gap toward the connecting arm. An arm interlocking feature is located at the circumferential arm and is configured to radially interlock with a complementary leg interlocking feature of the connecting leg. The arm interlocking feature and the leg interlocking feature have a radial interconnect gap therebetween in a free state.
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公开(公告)号：US20240301799A1
公开(公告)日：2024-09-12
申请号：US18118365
申请日：2023-03-07
发明人： Brandon W. Spangler
CPC分类号： F01D5/20 , F01D5/187 , F05D2240/305 , F05D2240/306 , F05D2240/307 , F05D2260/202
摘要： A blade for a gas turbine engine, including: an airfoil having a leading edge, a pressure side, a suction side and a trailing edge that extend to a tip of the airfoil; a leading edge cavity located within the airfoil; at least one main body cavity located within the airfoil; pressure side skin core passages located within the airfoil; suction side skin core passages located within the airfoil, the at least one main body cavity being fluidly isolated from the pressure side skin core passages and the suction side skin core passages and the at least one main body cavity being located between the pressure side skin core passages and the suction side skin core passages; a trailing edge feed cavity located within the airfoil; and a tip plenum located proximate to the tip of the airfoil, the tip plenum being fluidly coupled to the at least one main body cavity, wherein the tip plenum is located above the pressure side skin core passages and the trailing edge feed cavity and extends to the trailing edge of the airfoil.
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公开(公告)号：US20240293892A1
公开(公告)日：2024-09-05
申请号：US18117450
申请日：2023-03-05
发明人： Brian R. Craig , Paul E. Denney , Derek J. Bialka
IPC分类号： B23K26/0622 , B23K26/382 , B23K26/40
CPC分类号： B23K26/0622 , B23K26/382 , B23K26/40 , B23K2101/001 , B23K2103/52
摘要： A manufacturing method is provided during which a substrate aperture is formed through a substrate of a preform component for a turbine engine using a first machining process. A coating system is applied onto the substrate to provide a coated substrate. A coating aperture is formed through the coating system using a second machining process that is different than the first machining process. The second machining process includes percussion laser drilling. At least the substrate aperture and the coating aperture collectively form a cooling aperture through the coated substrate.
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公开(公告)号：US20240273845A1
公开(公告)日：2024-08-15
申请号：US18108844
申请日：2023-02-13
发明人： Luke B. Borkowski , Kevin L. Rugg
CPC分类号： G06T19/20 , G06T7/11 , G06T2207/10081 , G06T2219/2004 , G06T2219/2016
摘要： A method of analyzing computed tomography data includes creating a mesh of a sampling surface that extends through a component to obtain a meshed surface; creating a plurality of additional surfaces that are different from each other and from the meshed surface, and that each correspond to one or more of a translation and a rotation of the meshed surface; querying an interpolant function, which is fitted to CT data of the component, at a plurality of points of the meshed surface to project the CT data onto the meshed surface; querying the interpolant function at a plurality of points of the additional surfaces to project the CT data onto the additional surfaces; and determining, for each of the plurality of points of the meshed surface, whether the point is a void based on the querying for the meshed surface and the querying for the additional surfaces.
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公开(公告)号：US20240271784A1
公开(公告)日：2024-08-15
申请号：US18110186
申请日：2023-02-15
发明人： Orin G. Avidane , Andre M. Ajami , Coy Bruce Wood , Joseph V. Mantese , David L. Lincoln , Stephen K. Kramer , Ramesh Rajagopalan
CPC分类号： F23N5/082 , F23N1/005 , F23R3/28 , F23N2229/04 , F23N2229/16 , F23N2229/18
摘要： A combustion assembly for a gas turbine engine includes a combustor, a monochromator, and a photodetector assembly. The combustor forms a combustion chamber. The monochromator is disposed outside the combustion chamber. The monochromator is configured to receive an optical input from the combustion chamber and direct an optical output. The optical input has a range of light wavelengths. The optical output has a subset of the range of light wavelengths. The photodetector assembly is disposed outside the combustion chamber. The photodetector assembly is configured to receive the optical output from the monochromator and generate an output signal representative of one or more optical characteristics of the optical output.
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公开(公告)号：US20240271568A1
公开(公告)日：2024-08-15
申请号：US18108404
申请日：2023-02-10
发明人： Lawrence A. Binek , Sean R. Jackson
CPC分类号： F02C7/22 , F23R3/28 , F23D2900/11001
摘要： A system is provided for an aerial vehicle. This system includes a splash plate, a fuel nozzle and a gas circuit. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface. The gas circuit includes a gas passage and a gas outlet. At least a portion of the gas passage is formed by and embedded within the splash plate. The gas passage extends through the splash plate to the gas outlet.
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公开(公告)号：US20240261846A1
公开(公告)日：2024-08-08
申请号：US18107266
申请日：2023-02-08
CPC分类号： B21D53/04 , F28D9/0062 , F28F3/08
摘要： A method for making a heat exchanger includes machining a plate of material having a starting thickness and at least one alignment feature, the machining including machining down the starting thickness to produce a heat exchanger plate having at least one flow passage segment, and at least two ribs arranged extending along each side of the at least one flow segment; removing the at least one alignment feature to provide a trimmed heat exchanger plate; stacking the trimmed heat exchanger plate with a further heat exchanger plate with the at least two ribs interlocked with ribs of the further heat exchanger plate, and the at least one flow segment aligned with a flow segment of the further heat exchanger plate; and joining the at least two ribs of the trimmed heat exchanger plate and the ribs of the further heat exchanger plate together. The at least two ribs can be configured to interlock with ribs of an adjacent plate. Resulting heat exchangers can be produced wherein the plates define parting plate thicknesses that are thin and useful in space and weight constrained locations.
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公开(公告)号：US20240255383A1
公开(公告)日：2024-08-01
申请号：US18104756
申请日：2023-02-01
发明人： Eli Warren , Bryan J. Hackett
摘要： A measurement system is provided that includes a probe assembly. The probe assembly includes a capacitance probe and an optical probe. The capacitance probe includes a capacitance sensor that forms a sensor face of the probe assembly. An aperture projects axially through the capacitance sensor to the sensor face. The optical probe is configured with an optical line of sight through the aperture into a volume adjacent the sensor face.
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