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1.发明申请GAS TURBINE ENGINE COMPONENT COOLING CAVITY WITH VORTEX PROMOTING FEATURES 审中-公开气体涡轮发动机组件冷却空气与VORTEX促销功能
公开(公告)号：WO2015094531A1
公开(公告)日：2015-06-25
申请号：PCT/US2014/065858
申请日：2014-11-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： LORICCO, Nicholas M. , AUXIER, James T. , SNYDER, Brooks E. , SLAVENS, Thomas N.
CPC classification number: F01D5/189 , F01D5/187 , F01D5/284 , F01D9/02 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2230/50 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2250/25 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F05D2300/13 , F05D2300/20 , F23R3/002 , Y02T50/676
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a body, a wall extending inside of the body and a plurality of vortex promoting features arranged in a helical pattern along the wall.
Abstract translation: 根据本公开的示例性方面的部件包括主体，在主体内部延伸的壁和沿着壁布置成螺旋形图案的多个涡流促进特征。
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公开(公告)号：WO2020167598A1
公开(公告)日：2020-08-20
申请号：PCT/US2020/017174
申请日：2020-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： LORICCO, Nicholas M. , JARIWALA, Parth , SCHNEIDER, Alex J. , TELLER, Bret M. , GLEINER, Matthew S. , MORTON, Jeffrey T.
Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.
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公开(公告)号：WO2015094636A1
公开(公告)日：2015-06-25
申请号：PCT/US2014/068072
申请日：2014-12-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SLAVENS, Thomas N. , BLAKE, Mosheshe Camara-Khary , JENNINGS, Timothy J. , LORICCO, Nicholas M. , MOORE, Sasha M. , MUSTO, Clifford J.
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：WO2015073845A1
公开(公告)日：2015-05-21
申请号：PCT/US2014/065734
申请日：2014-11-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MOORE, Sasha M. , SLAVENS, Thomas N. , LORICCO, Nicholas M. , JENNINGS, Timothy J.
IPC: B24C1/10 , B24B27/033 , F01D5/12 , F01D5/20 , F01D9/02
CPC classification number: F01D5/187 , B24C3/327 , C23F1/16 , C23F1/32 , F01D9/02 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2300/506 , Y02T50/673 , Y02T50/676
Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.
Abstract translation: 本公开的一个示例性实施例涉及形成发动机部件的方法。 该方法包括形成具有内部通道的发动机部件，内部通路形成初始尺寸。 该方法还包括在内部通道内建立加工流体的流动，所述加工流体改变初始尺寸。
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公开(公告)号：WO2015013503A1
公开(公告)日：2015-01-29
申请号：PCT/US2014/047997
申请日：2014-07-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SLAVENS, Thomas N. , MOORE, Sasha M. , LORICCO, Nicholas M.
CPC classification number: F01D11/008 , F01D11/006 , F04D29/083 , F04D29/542 , F05D2220/32 , F05D2240/55 , F05D2250/75 , F16J15/06 , F16J15/062 , F16J15/0887
Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes at least one trough.
Abstract translation: 本公开涉及一种包括第一发动机部件和第二发动机部件的燃气涡轮发动机。 第一发动机部件具有与第二发动机部件的配合面相邻的配合面。 发动机还包括设置在第一发动机部件的配合面与第二发动机部件的配合面之间的密封件。 密封件包括至少一个槽。
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Patent Agency Ranking
公开(公告)号：WO2015077017A1
公开(公告)日：2015-05-28
申请号：PCT/US2014/064011
申请日：2014-11-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SNYDER, Brooks E. , SLAVENS, Thomas N. , LORICCO, Nicholas M. , AUXIER, James T.
CPC classification number: F01D5/187 , F01D5/181 , F01D5/182 , F01D5/186 , F05D2240/127 , F05D2260/2212
Abstract: A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.
Abstract translation: 燃气涡轮发动机部件包括提供内部冷却通道的相对的壁。 其中一个墙壁上有一个带有钩子的湍流器，它被封闭在墙壁内。
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7.发明申请
公开(公告)号：WO2014126674A1
公开(公告)日：2014-08-21
申请号：PCT/US2014/011833
申请日：2014-01-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SLAVENS, Thomas N. , THORNTON, Lane , MOORE, Sasha M. , LORICCO, Nicholas M.
CPC classification number: B22D19/0072 , B22C9/04 , B22C9/103 , F01D5/187 , F01D9/023 , F05D2230/211 , F05D2250/185 , F23R3/002 , Y02T50/676
Abstract: A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component.
Abstract translation: 一种制造组件的方法，其包括提供芯结构，围绕所述芯结构铸造部件，从所述铸造部件移除所述芯结构的第一部分，以及将所述芯结构的第二部分留在所述铸造部件中，以提供 减少铸件中的横截面积。
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公开(公告)号：EP3514332A1
公开(公告)日：2019-07-24
申请号：EP19153134.2
申请日：2019-01-22
Applicant: United Technologies Corporation
Inventor： LORICCO, Nicholas M. , TRINDADE, Ricardo , MONGILLO, Dominic J. Jr.
IPC: F01D5/18
Abstract: Components for gas turbine engines are provided. The components include a hot external wall (324a, 324b, 324c) that is exposed to hot gaspath air when installed within a gas turbine engine, and an interior impingement wall (320), wherein the interior impingement wall defines a feed cavity (316) and at least one impingement cavity (318a, 318b, 318c) is defined between the impingement wall and the external wall. The impingement wall includes a plurality of impingement holes (322) that fluidly connect the feed cavity to the at least one impingement cavity, the external wall includes a plurality of film holes (326a, 326b, 326c) that fluidly connect the at least one impingement cavity to an exterior surface of the external wall, and wherein the only source of cooling air within the at least one impingement cavity is the feed cavity.
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公开(公告)号：EP3514331A1
公开(公告)日：2019-07-24
申请号：EP19152897.5
申请日：2019-01-21
Applicant: United Technologies Corporation
Inventor： LORICCO, Nicholas M. , TRINDADE, Ricardo , MONGILLO, Dominic J.
Abstract: Airfoils (300) for gas turbine engines (20) are provided. The airfoils include an airfoil body (302) extending between a first platform (304) and a second platform (306), a first platform feed cavity (330) defined by the first platform, a second platform exit cavity (332) defined by the second platform, a first hybrid skin core cooling cavity passage (316) formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture (336) formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.
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公开(公告)号：EP3508693A1
公开(公告)日：2019-07-10
申请号：EP19150498.4
申请日：2019-01-07
Applicant: United Technologies Corporation
Inventor： LORICCO, Nicholas M.
Abstract: An airfoil for a gas turbine engine includes a cavity (84) including an internal surface (92) of an outer wall (90). A baffle (88) is disposed within the cavity (84) and spaced apart from the internal surface (92). A partition (94) is disposed between the baffle (88) and the internal surface (92) to divide a space between the baffle (88) and the internal surface (92) into at least a first passage (110) and a second passage (112).
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