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1. 发明申请

WO2015042009A1 MANUFACTURING METHOD FOR A BAFFLE-CONTAINING BLADE 审中-公开
标题翻译：包含叶片的制造方法
公开(公告)号：WO2015042009A1
公开(公告)日：2015-03-26
申请号：PCT/US2014/055765
申请日：2014-09-16
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SPANGLER, Brandon, W. , OTERO, Edwin
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/187 , F01D5/147 , F01D5/189 , F05D2220/32 , F05D2230/22 , F05D2230/31 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , F05D2300/606
摘要： A blade includes a platform and a monolithic airfoil extending from the platform to a tip. The airfoil includes a first wall extending from a leading edge to a trailing edge, a second wall extending from the leading edge to the trailing edge and joined to the first wall at the leading edge, and at least one rib extending from the first wall to the second wall. The at least one rib and the first and second walls define a cavity. The blade also includes a baffle positioned within the cavity. The baffle has walls that are separate and distinct from and not attached to the at least one rib and the first and second walls of the airfoil. A method for forming a blade includes forming a platform and forming an airfoil and a baffle within the airfoil on a layer-by-layer basis using additive manufacturing.
摘要翻译：叶片包括平台和从平台延伸到尖端的整体翼型件。翼型件包括从前缘延伸到后缘的第一壁，从前缘延伸到后缘并在前缘处连接到第一壁的第二壁以及从第一壁延伸到至少一个肋第二个墙。所述至少一个肋和所述第一壁和所述第二壁限定空腔。叶片还包括位于腔内的挡板。挡板具有与所述翼型件的至少一个肋部以及翼型件的第一和第二壁分开并且不连接的壁。用于形成叶片的方法包括使用添加剂制造在层叠的基础上形成平台并在翼型内形成翼型和挡板。

2. 发明申请

WO2015031057A1 GAS TURBINE ENGINE AIRFOIL CROSSOVER AND PEDESTAL RIB COOLING ARRANGEMENT 审中-公开
标题翻译：气体涡轮发动机空气冷却器和底盘冷却装置
公开(公告)号：WO2015031057A1
公开(公告)日：2015-03-05
申请号：PCT/US2014/050876
申请日：2014-08-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： OTERO, Edwin , LANA, Kyle C.
IPC分类号： F01D5/18 , F01D25/12 , F02C7/18 , F04D29/58
CPC分类号： F01D5/187 , F01D5/147 , F01D5/18 , F01D5/182 , F01D5/185 , F01D5/186 , F01D9/041 , F01D11/08 , F01D25/12 , F01D25/30 , F05D2220/32 , F05D2240/304 , F05D2240/35 , F05D2260/202 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F23R3/002 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction. The cross-over rib has holes that extend in a second direction transverse to the first direction. A row of at least one pedestal joins the walls and extends along the first direction. The row and the cross-over rib overlap one another in the second direction.
摘要翻译：燃气涡轮发动机部件包括间隔开的壁，其提供沿第一方向延伸的冷却通道。交叉肋连接壁并沿第一方向延伸。交叉肋具有沿与第一方向横切的第二方向延伸的孔。至少一个基座的一排连接壁并沿第一方向延伸。行和交叉肋在第二方向上彼此重叠。

3. 发明申请

WO2014099077A2 GAS TURBINE ENGINE ASYMMETRIC NOZZLE GUIDE VANES 审中-公开
标题翻译：气体涡轮发动机不对称喷嘴导向槽
公开(公告)号：WO2014099077A2
公开(公告)日：2014-06-26
申请号：PCT/US2013/061704
申请日：2013-09-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： GREGG, Shawn J. , OTERO, Edwin
CPC分类号： F02C3/14 , F23R3/28 , F23R3/50 , F23R2900/00014
摘要： A gas turbine engine includes a multiple of Nozzle Guide Vanes (NGVs) arranged asymmetrically and a multiple of NGVs clocked with respect to the multiple of fuel nozzles around a 360 degree circumference.
摘要翻译：燃气涡轮发动机包括多个非对称布置的喷嘴导向叶片（NGV），并且相对于围绕360度圆周的多个燃料喷嘴计时的多个NGV。

4. 发明申请

WO2014042735A2 GAS TURBINE ENGINE COMPONENT WITH DISCHARGE SLOT HAVING OVAL GEOMETRY 审中-公开
标题翻译：燃气轮机发动机部件与带有卵形几何的排气槽
公开(公告)号：WO2014042735A2
公开(公告)日：2014-03-20
申请号：PCT/US2013/046733
申请日：2013-06-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： BOEKE, Mark A. , OTERO, Edwin , DEGRAY, Jeffrey J. , PROPHETER-HINCKLEY, Tracy A. , FERNANDEZ, Guillermo J. , RILEY, Sarah
CPC分类号： F01D5/187 , F01D9/065 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2240/81 , F05D2250/14
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间延伸的主体部分。前缘和后缘中的至少一个包括至少一个排出槽，该排出槽具有包括椭圆形几何形状的第一部分。

5. 发明申请

WO2013133945A1 AIRFOIL WITH IMPROVED INTERNAL COOLING CHANNEL PEDESTALS 审中-公开
标题翻译：具有改进的内部冷却通道的AIRFOIL
公开(公告)号：WO2013133945A1
公开(公告)日：2013-09-12
申请号：PCT/US2013/026010
申请日：2013-02-14
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： OTERO, Edwin
IPC分类号： F01D5/18 , F01D25/10 , F02C7/12 , F02C7/00
CPC分类号： F01D5/187 , F01D5/188 , F05D2240/304 , F05D2250/14 , F05D2250/231 , F05D2260/202 , F05D2260/2214
摘要： An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.
摘要翻译：一种用于涡轮发动机的翼型件，所述翼型件包括第一侧壁，与第一侧壁间隔开的第二侧壁以及形成在第一侧壁和第二侧壁之间的内部冷却通道。内部冷却通道包括具有连接到第一侧壁的第一基座端和连接到第二侧壁的第二基座端的至少一个基座。内部冷却通道还包括在第一侧壁和第一基座端之间围绕第一基座端部的周边设置的第一圆角; 以及在所述第二侧壁和所述第二基座端之间围绕所述第二基座端部的周边设置的第二圆角。第一圆角和第二圆角中的至少一个包括在相应基座端的周边周围不均匀的轮廓。

6. 发明申请

WO2015034717A1 GAS TURBINE ENGINE AIRFOIL WITH WISHBONE BAFFLE COOLING SCHEME 审中-公开
标题翻译：燃气涡轮发动机空气与WISHBONE BAFFLE冷却方案
公开(公告)号：WO2015034717A1
公开(公告)日：2015-03-12
申请号：PCT/US2014/052854
申请日：2014-08-27
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SPANGLER, Brandon, W. , OTERO, Edwin
IPC分类号： F01D5/18 , F01D25/12 , F02C7/18 , F04D29/58
CPC分类号： F01D5/187 , B22C9/04 , B22C9/046 , B22C9/103 , B28B1/30 , B28B7/34 , F01D5/188 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2250/232 , F05D2250/75 , F05D2260/202 , F05D2260/221 , F05D2300/20 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.
摘要翻译：燃气涡轮发动机部件包括包括沿第一方向延伸到端壁的间隔开的第一和第二外壁的结构。第一和第二外壁在端壁处连接以提供冷却腔。叉骨挡板布置在冷却腔中，并且包括分别邻近第一和第二外壁的第一和第二内壁。第一和第二内壁沿第一方向延伸并由顶点连接以提供第一腔。叉骨挡板将第一腔与设置在顶点和端壁之间的第二腔分开。

7. 发明申请

WO2014052277A1 GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT 审中-公开
标题翻译：气体涡轮发动机空气冷却电路
公开(公告)号：WO2014052277A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/061321
申请日：2013-09-24
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SPANGLER, Brandon W. , ZELESKY, Mark F. , OTERO, Edwin
IPC分类号： F02C7/12 , F01D5/18 , F02K3/00
CPC分类号： F01D5/18 , F01D5/187 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。冷却回路设置在翼型的内部。冷却回路包括在翼型件内径向延伸的第一芯腔。第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤芯流体连通。

8. 发明申请

WO2013154657A2 TURBINE BLADE DAMPER SEAL 审中-公开
标题翻译：涡轮叶片减振器密封
公开(公告)号：WO2013154657A2
公开(公告)日：2013-10-17
申请号：PCT/US2013/023132
申请日：2013-01-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SNYDER, Daniel A. , LANA, Kyle, Charles , SANDOVAL, Jonathan, Perry , VIRKLER, Scott, Daniel , TARASKEVICH, Jaimie , OTERO, Edwin
IPC分类号： F01D11/00 , F01D5/14
CPC分类号： F01D5/22 , F01D5/3007 , F01D11/006 , Y02T50/673
摘要： A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.
摘要翻译：根据本公开的一个示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮叶片的空腔中的阻尼密封件包括中间主体部分，其具有第一端部区域，相对的第二端部区域和宽度。阻尼器密封件还包括从中央主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突片，该第一向外延伸的突片限定了第一扩大部分，该第一扩大部分具有大于中央主体部分和从中央主体部分的相对的第二端部区域延伸的第二部分。

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