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公开(公告)号：US10287900B2
公开(公告)日：2019-05-14
申请号：US15028572
申请日：2014-10-17
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Matthew A. Devore
Abstract: A disclosed turbine vane assembly for a gas turbine engine includes an airfoil including a pressure side and a suction side that extends from a leading edge toward a trailing edge. The airfoil is rotatable about an axis transverse to an engine longitudinal axis and includes a forward chamber within the airfoil and in communication with a cooling air source, a forward impingement baffle defining a pre-impingement cavity within the forward chamber. The pre-impingement cavity is split into a leading edge cavity, pressure side cavity and a suction side cavity defined between an inner surface of the forward chamber and an outer surface of the forward impingement baffle.
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12.发明授权公开(公告)号：US10247419B2
公开(公告)日：2019-04-02
申请号：US15665837
申请日：2017-08-01
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Mark F. Zelesky , Andrew D. Burdick
Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer ribs located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer ribs located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer ribs account for the multiple of studs.
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公开(公告)号：US20180291811A1
公开(公告)日：2018-10-11
申请号：US15479747
申请日：2017-04-05
Applicant: United Technologies Corporation
Inventor： Kevin L. Zacchera , Thomas N. Slavens
CPC classification number: F02C7/18 , B23P2700/06 , C23C4/01 , C23C14/042 , F01D5/186 , F01D5/288 , F05D2220/32 , F05D2230/237 , F05D2230/40 , F05D2230/90 , F05D2240/35 , F05D2260/202 , F05D2300/175 , F05D2300/20 , F23R3/002 , F23R2900/00018
Abstract: A method for applying a coating to a substrate having a plurality of holes. The method comprises: applying a braze material to a substrate having a plurality of holes; heating the substrate to melt the braze material to form a melt; cooling the substrate to solidify the melt to form plugs in the respective holes; applying a coating to the substrate; and further heating the substrate to melt the plugs.
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公开(公告)号：US20180023576A1
公开(公告)日：2018-01-25
申请号：US15218915
申请日：2016-07-25
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Arthur W. Utay , Tania Bhatia Kashyap , Thomas N. Slavens , Kevin L. Rugg , Mark F. Zelesky , Brian D. Merry , Gabriel L. Suciu
CPC classification number: B64D41/00 , F02C3/08 , F02C3/145 , F04D17/105
Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.
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公开(公告)号：US20170198838A1
公开(公告)日：2017-07-13
申请号：US14992646
申请日：2016-01-11
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Carey Clum
CPC classification number: F16L13/0209 , B23K1/0018 , B23K1/18 , B23K1/19 , B23K33/006 , B23K2101/001 , B23K2101/06 , B23K2103/05 , B23K2103/08 , F01D9/06 , F02C3/04 , F05D2220/32 , F05D2230/237
Abstract: Systems for tube-to-tube connections are described herein. A device having an aperture for receiving a tube may comprise: an inlet portion comprising a first diameter, the inlet portion located at an inlet of the aperture; a braze filler collector portion located axially adjacent to the inlet portion comprising a second diameter, the second diameter being greater than the first diameter; a necked portion located axially adjacent to the braze filler collector portion comprising a third diameter, the third diameter being less than the first diameter and the second diameter; a flow surface comprising a fourth diameter, the fourth diameter being less than the third diameter, the flow surface defining a void; and a collection pocket located axially adjacent to the necked portion, the collection pocket configured to collect a braze filler material from the necked portion to prevent the braze filler material from contacting the flow surface.
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Patent Agency Ranking
16.发明申请公开(公告)号：US20170051628A1
公开(公告)日：2017-02-23
申请号：US14827889
申请日：2015-08-17
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Carey Clum
CPC classification number: F01D17/105 , F01D5/18 , F01D25/10 , F01D25/12 , F02C7/185 , F05D2220/32 , F05D2260/213 , F05D2260/606 , F05D2270/3013 , F05D2270/3015
Abstract: A conduit system for a gas turbine engine includes, a heat exchanger configured to cool fluid flowing therethrough having an inlet and an outlet, at least one by-pass in operable communication with the heat exchanger that is configured to allow fluid to exit the heat exchanger before reaching the outlet, and a conduit that is in fluidic communication with the outlet and the at least one by-pass.
Abstract translation: 用于燃气涡轮发动机的管道系统包括：热交换器，其构造成冷却流过其中的流体具有入口和出口，至少一个旁路与热交换器可操作地连通，该热交换器构造成允许流体离开热交换器 在到达出口之前，以及与出口和至少一个旁路流体连通的导管。
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公开(公告)号：US09453419B2
公开(公告)日：2016-09-27
申请号：US13729110
申请日：2012-12-28
Applicant: United Technologies Corporation
Inventor： James T. Auxier , Jason L. O'Hearn , Thomas N. Slavens , Yafet Girma
CPC classification number: F01D5/186 , F01D5/20 , F01D11/08 , F05D2240/307 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.
Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端处的弧形线从前缘延伸到后缘。 压力和吸力侧搁板分别设置在压力侧和吸力侧壁的外倾线的相对侧的外表面上。 高原是为压力和吸力侧货架感到自豪和分离。 平台沿着弧形线布置并延伸到前缘。
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公开(公告)号：US20160265362A1
公开(公告)日：2016-09-15
申请号：US15030243
申请日：2014-10-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Mark F. Zelesky
IPC: F01D5/14 , B22D21/00 , B22F3/105 , B22F3/24 , B22F5/04 , B21K3/04 , B23K26/342 , B23K26/00 , B23K1/00 , B23K31/02 , B23K10/02 , B22D25/02 , B23K15/00
CPC classification number: F01D5/147 , B21K3/04 , B22D21/005 , B22D25/02 , B22F3/1055 , B22F3/24 , B22F5/04 , B22F7/08 , B22F2301/15 , B22F2301/20 , B22F2301/205 , B22F2301/35 , B22F2998/10 , B23K1/0018 , B23K10/027 , B23K15/0086 , B23K15/0093 , B23K26/0006 , B23K26/34 , B23K26/342 , B23K31/02 , B23K2101/001 , B23K2103/04 , B23K2103/08 , B23K2103/14 , B23K2103/16 , B33Y10/00 , B33Y80/00 , F01D5/188 , F05D2300/607 , Y02P10/295
Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.
Abstract translation: 本公开的一个示例性实施例涉及一种燃气涡轮发动机，其包括具有使用铸造和锻造工艺中的一种形成的第一部分的部件和使用添加剂制造工艺形成的第二部分。
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公开(公告)号：US20160222825A1
公开(公告)日：2016-08-04
申请号：US14917434
申请日：2014-09-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Steven Bruce Gautschi
Abstract: A pivoting turbine vane has an airfoil, an inner bearing race and an outer bearing race, with the inner and outer bearing races on a pivot axis of the pivoting turbine vane. There are cooling air passages through at least one of the inner and outer bearing races to provide cooling air from a remote facing face of at least one of the inner and outer bearing races to an airfoil facing face of at least one of the inner and outer bearing races. A turbine section is also disclosed.
Abstract translation: 枢转式涡轮叶片具有翼型件，内轴承座圈和外轴承座圈，其中内轴承座和外轴承座圈在枢转涡轮叶片的枢转轴线上。 存在通过内轴承座和外轴承座中的至少一个的冷却空气通道，以从内轴承座和外轴承座中的至少一个的远程面对面向内和外侧的至少一个的翼型面提供冷却空气 轴承赛。 还公开了涡轮机部分。
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公开(公告)号：US20160222794A1
公开(公告)日：2016-08-04
申请号：US14917879
申请日：2014-09-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Mark F. Zelesky , Atul Kohli , Sean D. Bradshaw , Steven Bruce Gautschi
IPC: F01D5/18 , F01D9/04 , F01D25/12 , F04D29/08 , F04D29/32 , F04D29/58 , F04D29/54 , F01D5/14 , F01D11/08
CPC classification number: F01D5/187 , F01D5/147 , F01D9/041 , F01D11/08 , F01D25/12 , F04D29/083 , F04D29/324 , F04D29/325 , F04D29/542 , F04D29/5846 , F05D2220/32 , F05D2240/303 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/202 , F05D2260/204
Abstract: This disclosure relates to a gas turbine engine including a component having a leading edge, a pressure side and a suction side opposite the pressure side. The component includes a first group of showerhead holes in the leading edge and a second group of showerhead holes in one of the pressure side and the suction side. The component further includes a first core passageway and a second core passageway separate from the first core passageway. The first core passageway and the second core passageway are in communication with a respective one of the first group of showerhead holes and the second group of showerhead holes.
Abstract translation: 本公开涉及一种燃气涡轮发动机，其包括具有前缘，压力侧和与压力侧相对的吸力侧的部件。 该部件包括在前缘中的第一组喷头孔和在压力侧和吸力侧之一中的第二组喷头孔。 该部件还包括与第一芯通道分开的第一芯通道和第二芯通道。 第一芯通道和第二芯通道与第一组喷头孔和第二组喷头孔中的相应一个连通。
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