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1.发明申请
公开(公告)号：WO2014116259A1
公开(公告)日：2014-07-31
申请号：PCT/US2013/023440
申请日：2013-01-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MCCAFFREY, Michael G. , PROPHETER-HINCKLEY, Tracy A. , SURACE, Raymond , SPANGLER, Brandon W.
IPC: F01D17/16
CPC classification number: F01D17/16 , F01D5/147 , F01D9/04 , F01D9/065 , F01D17/162 , F02C9/22 , F05D2260/201 , F05D2260/202
Abstract: An assembly for a turbine engine includes a plurality of vane segments. The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis. The adjustable stator vane includes a stator vane body, a shaft and a flange. The stator vane body extends axially between a first end and a second end, and includes an airfoil, a body surface and a cavity. The body surface is located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially at least partially around the inlet, and radially from the stator vane body. A first of the vane segments includes the flange. A second of the vane segments includes at least a portion of the airfoil.
Abstract translation: 涡轮发动机的组件包括多个叶片段。 叶片段被紧固在一起，并形成一个可调节的定子叶片，其绕可变叶片轴线枢转。 可调节定子叶片包括定子叶片体，轴和凸缘。 定子叶片体在第一端和第二端之间轴向延伸，并且包括翼型件，主体表面和空腔。 身体表面位于第一端。 空腔从体表面的入口轴向延伸到翼型中。 轴从第一端沿着可变叶片轴线延伸。 凸缘至少部分地围绕入口周向延伸，并且从定子叶片体径向延伸。 第一叶片段包括凸缘。 叶片段中的第二个叶片包括翼型的至少一部分。
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公开(公告)号：WO2013163020A1
公开(公告)日：2013-10-31
申请号：PCT/US2013/037318
申请日：2013-04-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ZELESKY, Mark, F. , PROPHETER-HINCKLEY, Tracy A. , MONGILLO, JR., Dominic J. , GAUTSCHI, Steven Bruce , DEVORE, Matthew A. , FISK, Benjamin T.
CPC classification number: B22C9/10 , B22C9/04 , B22F3/1055 , B22F3/24 , B22F5/04 , B22F2003/242 , B33Y10/00 , B33Y40/00 , C22C1/045 , F01D5/187 , F05D2230/22 , Y02P10/292 , Y02P10/295 , Y10T29/49337
Abstract: A core has a body that includes a cooling passage portion with a film cooling passage portion extending there from to a film cooling hole portion. An exterior airfoil portion is connected to the film cooling hole portion and is spaced apart from the cooling passage portion to provide a space surrounding the film cooling hole portion that corresponds to an exterior airfoil wall.
Abstract translation: 芯部具有包括冷却通道部分的主体，其中薄膜冷却通道部分从该冷却通道部分延伸到薄膜冷却孔部分。 外部翼型部分连接到薄膜冷却孔部分并且与冷却通道部分间隔开，以提供对应于外部翼型壁的薄膜冷却孔部分周围的空间。
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公开(公告)号：WO2020117428A1
公开(公告)日：2020-06-11
申请号：PCT/US2019/060701
申请日：2019-11-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： PROPHETER-HINCKLEY, Tracy A.
Abstract: An investment casting core system includes first and second investment casting cores. The first investment casting core has a pin and the second investment casting core has a hole and an access slot that opens to the hole. The pin is disposed in the hole such as to space the first investment casting core in a fixed position relative to the second investment casting core. A bonding agent is disposed in the access slot and around the pin in the hole.
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公开(公告)号：WO2015053846A2
公开(公告)日：2015-04-16
申请号：PCT/US2014/049749
申请日：2014-08-05
Applicant: UNITED TECHNOLOGIES CORPORATION
CPC classification number: F01D25/12 , F01D5/12 , F01D5/187 , F01D9/041 , F01D11/006 , F01D11/08 , F04D29/324 , F04D29/38 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2230/21 , F05D2230/211 , F05D2230/30 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/2212 , F05D2300/13 , F05D2300/20 , Y02T50/676
Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a component. The component includes a platform having a mateface on a circumferential side thereof. The platform including a core passageway configured to communicate fluid to the mateface.
Abstract translation: 本公开的一个示例性实施例涉及包括部件的燃气涡轮发动机。 该部件包括在其圆周侧上具有接合面的平台。 该平台包括配置成将流体传送到配合面的芯通道。
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公开(公告)号：WO2014150365A1
公开(公告)日：2014-09-25
申请号：PCT/US2014/023062
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： PROPHETER-HINCKLEY, Tracy A. , DONNELL, Brandon S.
CPC classification number: B22F5/009 , B22F3/1055 , B22F5/04 , B22F2003/1056 , B33Y10/00 , B33Y30/00 , B33Y80/00 , F01D5/147 , F01D5/188 , F01D5/189 , F01D9/041 , F01D9/065 , F05D2220/32 , F05D2230/22 , F05D2230/234 , F05D2230/50 , F05D2260/20 , Y02P10/295
Abstract: A method includes (a) depositing a layer of a powder material on a work stage, the layer having a thickness, (b) solidifying a portion of the layer based upon data that defines an insert with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage by the thickness. Steps (a) - (c) can then be repeated until the insert is complete. The insert can then be removed from the work stage. An insert formed by the above process is also disclosed.
Abstract translation: 一种方法包括（a）在工作台上沉积粉末材料层，所述层具有厚度，（b）基于限定具有本体的插入物的数据固化该层的一部分，该主体被成形为适合于 燃气涡轮发动机部件中的腔，以及（c）将工作台降低厚度。 然后可以重复步骤（a） - （c），直到插入物完成。 然后可以将该插入物从工作台移除。 还公开了通过上述方法形成的插入物。
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Patent Agency Ranking6.发明申请GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE 审中-公开具有瓦斯工程尺寸结构的气体涡轮发动机部件
公开(公告)号：WO2014105108A1
公开(公告)日：2014-07-03
申请号：PCT/US2013/032003
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MONGILLO, Dominic J. , PROPHETER-HINCKLEY, Tracy A. , ZELESKY, Mark F. , WAGNER, Joel H. , SLAVENS, Thomas N.
CPC classification number: F01D5/186 , B22F3/1055 , B23P15/26 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D5/147 , F01D5/18 , F01D5/183 , F01D5/184 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/08 , F01D25/24 , F02C7/18 , F05D2250/185 , F05D2260/204 , Y10T29/49318 , Y10T29/49337 , Y10T29/49343 , Y10T29/49352 , Y10T428/249921
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure.
Abstract translation: 根据本公开的示例性方面的部件尤其包括形成在壁内部的壁和血管工程格子结构。 血管工程格子结构限定了中空血管结构，其构造成使流体通过血管工程化晶格结构。 血管工程格子结构具有至少一个入口孔和至少一个出口孔，其将流体与中空血管结构连通。
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公开(公告)号：WO2014058509A2
公开(公告)日：2014-04-17
申请号：PCT/US2013/051788
申请日：2013-07-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： PROPHETER-HINCKLEY, Tracy A. , HANSEN, Eric A.
Abstract: A casting core assembly (140) includes a metallic core (144, 146, 148; 360; 380; 400) and a ceramic core (142). A protuberant portion (184) of a metallic core is received in compartment (186) of the ceramic core.
Abstract translation: 铸造芯组件（140）包括金属芯（144,146,148; 360; 380; 400）和陶瓷芯（142）。 金属芯的突起部分（184）被容纳在陶瓷芯的隔室（186）中。
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公开(公告)号：WO2013162887A1
公开(公告)日：2013-10-31
申请号：PCT/US2013/035939
申请日：2013-04-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： FISK, Benjamin T. , PROPHETER-HINCKLEY, Tracy A. , DOLANSKY, Gregory M. , HOUSTON, David P. , TRACY, Anita L.
CPC classification number: F01D5/16
Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.
Abstract translation: 翼型件包括具有前缘和后缘的翼型件主体和与第一侧壁间隔开的第一侧壁和第二侧壁。 第一侧壁和第二侧壁连接前缘和后缘，并且至少部分地限定翼型本体中的空腔。 阻尼器构件被封闭在空腔中并且在空腔内自由浮动。
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9.发明申请GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE 审中-公开具有瓦斯工程尺寸结构的气体涡轮发动机部件
公开(公告)号：WO2014105113A1
公开(公告)日：2014-07-03
申请号：PCT/US2013/041054
申请日：2013-05-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MONGILLO, Dominic J. , PROPHETER-HINCKLEY, Tracy A.
CPC classification number: F01D5/186 , B22F3/1055 , B23P15/26 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D5/147 , F01D5/18 , F01D5/183 , F01D5/184 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/08 , F01D25/24 , F02C7/18 , F05D2250/185 , F05D2260/204 , Y10T29/49318 , Y10T29/49337 , Y10T29/49343 , Y10T29/49352 , Y10T428/249921
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.
Abstract translation: 根据本公开的示例性方面的部件尤其包括形成在壁内部的壁和血管工程格子结构。 血管工程化晶格结构包括中空血管结构和固体血管结构中的至少一个，其被配置为使流体通过血管工程化晶格结构传播。
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10.发明申请GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE 审中-公开具有血管工程网格结构的燃气涡轮发动机组件
公开(公告)号：WO2014105109A1
公开(公告)日：2014-07-03
申请号：PCT/US2013/032202
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ZELESKY, Mark F. , WAGNER, Joel H. , PROPHETER-HINCKLEY, Tracy A. , BLAIR, Michael F. , SLAVENS, Thomas N. , MONGILLO, Dominic J.
CPC classification number: F01D5/186 , B22F3/1055 , B23P15/26 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D5/147 , F01D5/18 , F01D5/183 , F01D5/184 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/08 , F01D25/24 , F02C7/18 , F05D2250/185 , F05D2260/204 , Y10T29/49318 , Y10T29/49337 , Y10T29/49343 , Y10T29/49352 , Y10T428/249921
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.
Abstract translation: 除了别的以外，根据本公开的示例性方面的部件包括在壁内部形成的壁和血管工程晶格结构。 血管工程化的晶格结构包括中空血管结构和实心血管结构中的至少一种，其被配置为将流体传送通过血管工程化晶格结构。
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