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公开(公告)号：US11602791B2
公开(公告)日：2023-03-14
申请号：US16131700
申请日：2018-09-14
IPC分类号： B22F10/20 , B22F10/28 , B33Y70/10 , B23K26/00 , B23K26/06 , B22F1/16 , B22F1/054 , B22F10/30
摘要： A process for additive manufacturing of a metal alloy material is provided that includes: a) providing a feedstock powder comprising base powder particles with nanoparticles attached to surfaces of the base powder particles; b) providing an additive manufacturing system with a laser power source relatively movable at a scan speed; c) wherein the additive manufacturing system has a process window for the feedstock powder; and d) exposing the feedstock powder to a predetermined power input from the laser power source at a predetermined scan speed to produce the metal alloy material. The concentration by volume of nanoparticles within the feedstock powder is such that independent first and second microstructures may be produced within the metal alloy material.
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公开(公告)号：US11583928B2
公开(公告)日：2023-02-21
申请号：US16385177
申请日：2019-04-16
IPC分类号： B33Y50/02 , B22F10/20 , B29C64/386 , G06F30/20 , B22F5/00 , B22F5/04 , B33Y10/00 , B33Y30/00 , B33Y80/00 , G06F119/18
摘要： A method of additively manufacturing includes generating a thermal model driven scan map that identifies an equiaxed cap region, a single crystal (SX) region, and a columnar to equiaxed transition (CET) region; and forming an active melt pool with respect to the thermal model driven scan map such that a depth of the active melt pool is greater than a thickness of the equiaxed transition (CET) region.
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公开(公告)号：US11162416B2
公开(公告)日：2021-11-02
申请号：US16222109
申请日：2018-12-17
发明人： Evan Butcher , Jesse R. Boyer , Om P. Sharma , Lawrence Binek , Bryan G. Dods , Vijay Narayan Jagdale
IPC分类号： F02C6/20 , F01D25/24 , B60K3/04 , B33Y10/00 , B33Y80/00 , F01D25/26 , F01D25/28 , F02C7/20 , F02K1/80
摘要： A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.
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公开(公告)号：US20180348736A1
公开(公告)日：2018-12-06
申请号：US15613750
申请日：2017-06-05
发明人： John A. Sharon , Vijay Narayan Jagdale , Sergei F. Burlatsky , David Ulrich Furrer , Tahany Ibrahim El-Wardany , Ranadip Acharya , Alexander Staroselsky
IPC分类号： G05B19/4099 , B29C67/00
CPC分类号： B22F3/1055 , B22F2003/1057 , B29C64/153 , B29C64/386 , B33Y10/00 , B33Y30/00 , B33Y50/00 , G06F17/50 , G06F17/5009
摘要： A method includes accessing a first model defining a shape of a part. The shape of the part is segregated into a plurality of predefined shapes selected from a library of predefined shapes. The predefined models for each of plurality of predefined shapes are assembled into a second model defining the shape of the part. The part is additively manufactured according to the second model.
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公开(公告)号：US20200331059A1
公开(公告)日：2020-10-22
申请号：US16385177
申请日：2019-04-16
IPC分类号： B22F3/105 , B29C64/386 , G06F17/50 , B22F5/00 , B22F5/04
摘要： A method of additively manufacturing includes generating a thermal model driven scan map that identifies an equiaxed cap region, a single crystal (SX) region, and a columnar to equiaxed transition (CET) region; and forming an active melt pool with respect to the thermal model driven scan map such that a depth of the active melt pool is greater than a thickness of the equiaxed transition (CET) region.
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公开(公告)号：US20200088408A1
公开(公告)日：2020-03-19
申请号：US16130837
申请日：2018-09-13
发明人： Lawrence Binek , Evan Butcher , Matthew B. Kennedy , Vijay Narayan Jagdale , Jesse R. Boyer , Dmytro Mykolayovych Voytovych
摘要： A component for a gas turbine engine is disclosed. In various embodiments, the component includes a diffuser ring, a combustor and a spring element connecting the diffuser ring to the combustor.
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公开(公告)号：US11199136B2
公开(公告)日：2021-12-14
申请号：US16152848
申请日：2018-10-05
发明人： Evan Butcher , Jesse R. Boyer , Om P. Sharma , Lawrence Binek , Bryan G. Dods , Vijay Narayan Jagdale
摘要： An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.
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公开(公告)号：US11174744B2
公开(公告)日：2021-11-16
申请号：US16148616
申请日：2018-10-01
发明人： Lawrence Binek , Tommy Skiba , Matthew B. Kennedy , Evan Butcher , Jesse R. Boyer , Vijay Narayan Jagdale , Dmytro Mykolayovych Voytovych
摘要： An assembly for use in an attritable engine includes a hub and a blade. The hub is configured to rotate about a centerline axis passing through a center of the hub and is formed with a first type of layer-by-layer additive manufacturing process. The blade is connected to and extends radially outward from the hub. The blade is formed with a second type of layer-by-layer additive manufacturing process that is different than the first layer-by-layer additive manufacturing process. The hub and the blade are integrally formed together as a single piece of material with a layer-by-layer additive manufacturing process. The blade includes a root of a first material, a platform connected to the root, an airfoil connected to and extending from the platform, and a tip connected on a distal end of the airfoil opposite from the root. The platform includes a material that is different from the first.
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公开(公告)号：US11156156B2
公开(公告)日：2021-10-26
申请号：US16151728
申请日：2018-10-04
发明人： Lawrence Binek , Jesse R. Boyer , Om P. Sharma , Evan Butcher , Bryan G. Dods , Vijay Narayan Jagdale
摘要： A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.
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公开(公告)号：US10989408B2
公开(公告)日：2021-04-27
申请号：US16130837
申请日：2018-09-13
发明人： Lawrence Binek , Evan Butcher , Matthew B. Kennedy , Vijay Narayan Jagdale , Jesse R. Boyer , Dmytro Mykolayovych Voytovych
摘要： A component for a gas turbine engine is disclosed. In various embodiments, the component includes a diffuser ring, a combustor and a spring element connecting the diffuser ring to the combustor.
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