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公开(公告)号：US09957810B2
公开(公告)日：2018-05-01
申请号：US14852896
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Clifford J. Musto , Nicholas M. LoRicco , Thomas N. Slavens , Timothy J. Jennings , Carey Clum , Sasha M. Moore , John McBrien , San Quach , Christopher Whitfield
CPC classification number: F01D5/186 , B22C9/10 , B33Y10/00 , B33Y80/00 , F01D5/187 , F05D2230/21 , F05D2230/22 , F05D2230/31 , F05D2240/127 , F05D2260/202 , F05D2260/2212 , Y02T50/676
Abstract: A wall of a gas turbine engine is provided. The wall may comprise an external surface adjacent a gas path and an internal surface adjacent an internal flow path. A film hole may have an inlet at the internal surface and an outlet at the external surface. A flow accumulator adjacent the inlet may protrude from the internal surface. A method of making an engine component is also provided and comprises the step of forming a component wall comprising an accumulator on an internal surface and a film hole defined by the component wall. The film hole may include an opening adjacent the accumulator and defined by the internal surface.
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公开(公告)号：US20180013959A1
公开(公告)日：2018-01-11
申请号：US15205874
申请日：2016-07-08
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Jeremy Styborski , Alex J. Schneider , Lea Kennard Castle , Rodney H. Warner , James Tilsley Auxier
CPC classification number: H04N5/33 , G01F9/00 , G01M15/14 , G01N25/72 , G06T7/0006 , G06T7/0081 , G06T2200/08 , G06T2207/10048 , G06T2207/30164
Abstract: A method for evaluating a turbine component includes inducing a thermal response of the component at an initial time, capturing a two-dimensional infrared image of the thermal response of the component with a thermal imaging device, wherein the two-dimensional infrared image comprises a plurality of infrared image pixels, generating a two-dimension to three-dimension mapping template to correlate two-dimensional infrared image data with three-dimensional locations on the component, mapping at least a subset of the plurality of infrared image pixels of the two-dimensional infrared image to three-dimensional coordinates using the mapping template, and generating a three-dimensional infrared image and infrared data of the component from the mapped infrared image pixels to three-dimensional coordinates, wherein the three-dimensional infrared image and infrared data is used to qualify the component for use.
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公开(公告)号：US09713843B2
公开(公告)日：2017-07-25
申请号：US15111421
申请日：2015-01-14
Applicant: United Technologies Corporation
Inventor： Brooks E. Snyder , Thomas N. Slavens
IPC: B22F3/105 , B22F5/04 , F01D25/12 , B33Y10/00 , B33Y80/00 , B22F5/00 , B23K15/00 , F01D5/18 , F01D9/02 , F01D11/08 , B23K101/00
CPC classification number: B22F3/1055 , B22F5/009 , B22F5/04 , B22F2998/10 , B23K15/0086 , B23K2101/001 , B33Y10/00 , B33Y80/00 , F01D5/18 , F01D9/02 , F01D11/08 , F01D25/12 , F05D2220/30 , F05D2230/22 , F05D2230/31 , F05D2240/11 , F05D2260/204 , F05D2300/10 , Y02P10/295
Abstract: A method of additively manufacturing is used to produce a component with an internal cooling channel for conveying a fluid. Powders in a powder bed are selectively fused to form a shaped layer of a body of the cooled component. The fusing is repeated on a layer-by-layer basis to form the body of the component with the internal cooling channel extending within the body, so that a peripheral wall of the internal cooling channel has a geometry that allows the peripheral wall to be self-supporting.
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公开(公告)号：US20170198636A1
公开(公告)日：2017-07-13
申请号：US14991064
申请日：2016-01-08
Applicant: United Technologies Corporation
Inventor： Carey Clum , Thomas N. Slavens
CPC classification number: F02C7/18 , F01D5/081 , F01D5/082 , F01D25/12 , F05D2220/32 , F05D2230/00 , F05D2230/60 , F05D2260/20 , Y02T50/676
Abstract: A tangential on-board injector (TOBI) for a gas turbine engine and methods of making the same are provided. The TOBI includes at least one adjustable strut configured to control an airflow through the TOBI, the at least one adjustable strut moveable to change an airflow characteristic within the TOBI.
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75.发明申请公开(公告)号：US20170173671A1
公开(公告)日：2017-06-22
申请号：US14976333
申请日：2015-12-21
Applicant: United Technologies Corporation
Inventor： James Tilsley Auxier , Thomas N. Slavens
CPC classification number: B22C9/103 , B22C9/24 , B22D23/06 , B22D27/045 , B22F3/1055 , B22F5/007 , B22F7/02 , B22F7/08 , B28B1/001 , B28B7/346 , B33Y10/00 , B33Y80/00 , C30B1/02 , Y02P10/292 , Y02P10/295
Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes an additively manufactured skeleton core portion manufactured of a refractory metal, a surround core portion that at least partially encapsulates the additively manufactured skeleton core portion, the surround core portion manufactured of a ceramic material, a surround core portion that at least partially encapsulates the additively manufactured skeleton core portion, the surround core portion manufactured of a ceramic material and a cooling hole shape that extends from the additively manufactured skeleton core portion through the surround core portion, the cooling hole shape operable to form a cooling hole.
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Patent Agency Ranking
公开(公告)号：US20160312617A1
公开(公告)日：2016-10-27
申请号：US15102890
申请日：2014-12-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Mosheshe Camara-Khary Blake , Timothy J. Jennings , Nicholas M. LoRicco , Sasha M. Moore , Clifford J. Musto
CPC classification number: F01D5/147 , F01D5/187 , F01D5/20 , F01D5/284 , F05D2230/30 , F05D2260/202 , F05D2300/13 , F05D2300/17 , F05D2300/6031 , F05D2300/6033 , F05D2300/606 , F05D2300/607
Abstract: A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.
Abstract translation: 用于燃气涡轮发动机的叶片包括将跨度从根延伸到尖端的翼型件。 机翼由靠近根部的第一部分提供，并具有金属合金。 尖端附近的第三部分具有耐火材料。 第二部分连接第一和第三部分并且具有功能分级材料。
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公开(公告)号：US20160298462A1
公开(公告)日：2016-10-13
申请号：US14682207
申请日：2015-04-09
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Thomas N. Slavens
CPC classification number: F01D5/186 , B22C9/24 , F01D9/041 , F01D11/08 , F01D25/12 , F02C3/00 , F02C7/18 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/22 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2260/202 , Y02T50/676
Abstract: A gas turbine engine component includes a wall which includes a first surface and a second surface opposing the first surface. A plurality of cooling passages extends between the first surface and the second surface each including a metering portion and a diffusion portion. The diffusion portion includes a cast or as-consolidated surface.
Abstract translation: 燃气涡轮发动机部件包括壁，该壁包括第一表面和与第一表面相对的第二表面。 多个冷却通道在第一表面和第二表面之间延伸，每个包括计量部分和扩散部分。 扩散部分包括铸造或固结表面。
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公开(公告)号：US20160265366A1
公开(公告)日：2016-09-15
申请号：US15032736
申请日：2014-10-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brooks E. Snyder , Thomas N. Slavens
IPC: F01D5/18 , B22D25/02 , B22F3/105 , B23K15/00 , B23K26/342
CPC classification number: F01D5/187 , B22D25/02 , B22F3/1055 , B22F5/04 , B22F7/08 , B23K15/0086 , B23K26/342 , B33Y10/00 , B33Y80/00 , F01D5/20 , F05D2220/32 , F05D2230/211 , F05D2230/22 , F05D2230/31 , F05D2240/307 , F05D2250/10 , F05D2260/201 , F05D2260/202 , Y02P10/295
Abstract: A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.
Abstract translation: 燃气涡轮发动机部件包括具有被配置为暴露于热工作流体的表面的结构。 表面包括被突出部限定的凹进的凹口。 至少一个冷却槽由突出部提供。
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公开(公告)号：US20160251980A1
公开(公告)日：2016-09-01
申请号：US15028468
申请日：2014-10-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Steven Bruce Gautschi
CPC classification number: F01D25/12 , F01D5/02 , F01D5/12 , F01D9/041 , F01D11/001 , F01D11/04 , F01D17/14 , F01D17/162 , F02C3/04 , F05D2220/32 , F05D2240/35 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2260/20
Abstract: A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.
Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮叶片组件，并且包括可围绕横向于发动机纵向轴线的第一轴线旋转的翼型件。 翼型件包括端壁和设置在端壁上的至少一个突出部，其构造成阻止流过端壁与燃气涡轮发动机的静态结构之间的间隙。
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公开(公告)号：US20160169005A1
公开(公告)日：2016-06-16
申请号：US14923553
申请日：2015-10-27
Applicant: United Technologies Corporation
Inventor： San Quach , Christopher King , Thomas N. Slavens
CPC classification number: F01D5/187 , F01D5/02 , F01D5/186 , F01D9/041 , F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2230/10 , F05D2240/12 , F05D2240/30 , F05D2240/307 , F05D2240/35 , F05D2250/231 , F05D2250/232 , F05D2260/202 , F23R3/002 , Y02T50/676
Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.
Abstract translation: 用于燃气涡轮发动机的冷却回路包括燃气涡轮发动机部件，其具有主体，该主体具有由空腔壁限定的至少一个内部空腔。 多个冷却孔形成在空腔壁内，其中每个冷却孔由从冷却孔入口延伸到冷却孔出口的长度限定，并且其中冷却孔相对于彼此定位，使得最小允许韧带距离 沿着每个冷却孔的整个长度保持在相邻的冷却孔之间。 还公开了一种燃气涡轮发动机和形成燃气涡轮发动机的冷却回路的方法。
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