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1. 发明申请

WO2015088699A8 GAS TURBINE ENGINE COMPONENT MATEFACE SURFACES 审中-公开
标题翻译：燃气轮机发动机部件表面粗糙度曲面
公开(公告)号：WO2015088699A8
公开(公告)日：2015-06-18
申请号：PCT/US2014/065430
申请日：2014-11-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： LEWIS, Scott D. , KOHLI, Atul , PRAISNER, Thomas J.
IPC分类号： F01D25/00 , F01D5/14 , F01D5/22 , F01D5/30 , F01D9/02 , F01D11/08
摘要： An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively have first and second rounded edges at the gap that are arranged in staggered relationship relative to one another.
摘要翻译：燃气涡轮发动机中的部件阵列包括第一结构和第二结构，第一结构和第二结构分别包括彼此相邻布置以提供间隙的第一表面和第二表面。第一和第二表面分别在间隙处具有第一和第二圆形边缘，这些边缘相对于彼此以交错关系布置。

2. 发明申请

WO2013115871A1 GAS TURBINE ENGINE MID TURBINE FRAME WITH FLOW TURNING FEATURES 审中-公开
标题翻译：气体涡轮发动机中间涡轮机框架与流动特性
公开(公告)号：WO2013115871A1
公开(公告)日：2013-08-08
申请号：PCT/US2012/063837
申请日：2012-11-07
申请人： UNITED TECHNOLOGIES CORPORATION , PRAISNER, Thomas J. , MAGGE, Shankar S. , ESTES, Matthew B.
发明人： PRAISNER, Thomas J. , MAGGE, Shankar S. , ESTES, Matthew B.
IPC分类号： F01D9/04 , F02C3/04
CPC分类号： F01D9/041 , F01D5/141 , F01D9/04 , F01D9/065 , F01D25/28 , F02K3/06 , F05D2240/12 , Y02T50/673
摘要： A gas turbine engine includes first and second stages having a rotational axis. A mid turbine frame is arranged axially between the first and second stages. The mid turbine frame includes a circumferential array of airfoils, and the airfoils each have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°, for example. In one example, an airfoil aspect ratio is less than 1.5.
摘要翻译：燃气涡轮发动机包括具有旋转轴线的第一和第二级。中间涡轮机框架轴向布置在第一和第二阶段之间。中间涡轮机框架包括圆周阵列的翼型件，翼型件各自具有在压力侧和吸力侧之间等距离设置的曲率。翼型件沿着翼型在中跨平面处从前缘延伸到后缘。在与翼面前缘和后缘处的平面和曲率的交点相切的第一和第二线之间限定角度。该角度例如等于或大于约10°。在一个示例中，翼型长宽比小于1.5。

3. 发明申请

WO2014074199A3 ROOT BOW GEOMETRY FOR AIRFOIL SHAPED VANE 审中-公开
公开(公告)号：WO2014074199A3
公开(公告)日：2014-05-15
申请号：PCT/US2013/055726
申请日：2013-08-20
申请人： UNITED TECHNOLOGIES CORPORATION , MTU AERO ENGINES GMBH
发明人： JUREK, Renee J. , PRAISNER, Thomas J. , HOEGER, Martin
IPC分类号： F01D5/14 , F02C7/20
摘要： A vane assembly used for controlling a turning gas flow includes multiple vanes, each of which is bowed toward a pressure side of the vane at the root of the vane.

4. 发明申请

WO2013130181A2 LOW LOSS AIRFOIL PLATFORM TRAILING EDGE 审中-公开
标题翻译：低损失航空平台行驶边
公开(公告)号：WO2013130181A2
公开(公告)日：2013-09-06
申请号：PCT/US2013/020962
申请日：2013-01-10
申请人： UNITED TECHNOLOGIES CORPORATION , AGGARWALA, Andrew S. , PRAISNER, Thomas J.
发明人： AGGARWALA, Andrew S. , PRAISNER, Thomas J.
IPC分类号： F01D5/20 , F01D5/14
CPC分类号： F01D5/143 , F05D2240/80 , F05D2260/60 , Y02T50/673
摘要： An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform.
摘要翻译：翼型平台包括前缘部分和后缘部分。后缘部分包括具有凸形流路轮廓的第一区域，具有从凸形流路轮廓的下游延伸的中间流路轮廓的第二区域以及具有从中间流路轮廓向下延伸的凹或线性流路轮廓的第三区域平台的后缘部分的下游端。

5. 发明申请

WO2014130214A1 STATOR VANE ASSEMBLY AND METHOD THEREFORE 审中-公开
标题翻译：定子风扇组件及其方法
公开(公告)号：WO2014130214A1
公开(公告)日：2014-08-28
申请号：PCT/US2014/013276
申请日：2014-01-28
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FARAH, Jorge I. , BURT, Jonathan P. , PRAISNER, Thomas J.
IPC分类号： F01D9/02 , F02C7/00
CPC分类号： F01D9/047 , F01D25/162 , F02C7/20 , F05D2230/23 , F05D2240/12 , F05D2240/80
摘要： A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.
摘要翻译：定子叶片组件包括多个不同的叶片段，每个叶片段分别包括第一平台，第二平台和至少一个叶片翼型件，其相对的端部连接到第一平台和第二平台。第一平台在不同的第一接头彼此相交，并且第二平台在彼此不同的第二接头处相交，使得多个叶片段形成环形结构。

6. 发明申请

WO2014007994A1 AIRFOIL FOR IMPROVED FLOW DISTRIBUTION WITH HIGH RADIAL OFFSET 审中-公开
标题翻译：用于改进流量分布的高空心偏置的气翼
公开(公告)号：WO2014007994A1
公开(公告)日：2014-01-09
申请号：PCT/US2013/046766
申请日：2013-06-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： PRAISNER, Thomas J. , MODESTO-MADERA, Noel
IPC分类号： F02K1/00 , F02K1/38 , F02K99/00
CPC分类号： F01D5/12 , F01D5/141 , F01D9/041 , Y02T50/673
摘要： A vane assembly for use in a gas flow duct. The vane assembly includes multiple vanes arranged circumferentially about the duct. A throat angle of each of the vanes at mid-span is greater than the throat angel at the tips of the vane.
摘要翻译：用于气流管道的叶片组件。叶片组件包括围绕管道周向布置的多个叶片。中跨的每个叶片的喉部角度大于叶片尖端处的喉部角度。

7. 发明申请

WO2015147930A2 TURBINE AIRFOIL COOLING 审中-公开
标题翻译：涡轮机叶片冷却
公开(公告)号：WO2015147930A2
公开(公告)日：2015-10-01
申请号：PCT/US2014/071582
申请日：2014-12-19
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： CHAKKA, Pitchaiah Vijay , AGGARWALA, Andrew S. , PRAISNER, Thomas J. , SPANGLER, Brandon W.
IPC分类号： F01D5/18 , F02C7/16
CPC分类号： F01D25/12 , F01D5/12 , F01D5/145 , F01D9/02 , F02C3/04 , F05D2220/323 , F05D2240/35 , F05D2240/81 , F05D2260/20 , Y02T50/673 , Y02T50/676
摘要： An airfoil assembly has at least one cooling hole in an aft edge of at least one platform for cooling at least one of an axially downstream airfoil root and/or tip region. The airfoil assembly may be a high pressure turbine first stage vane coupled with a combustor operating at a low Pattern Factor.
摘要翻译：翼型组件在至少一个平台的后缘中具有至少一个冷却孔，用于冷却轴向下游翼型根部和/或尖端区域中的至少一个。翼型组件可以是高压涡轮第一级叶片，其与在低图案因数下操作的燃烧器耦合。

8. 发明申请

WO2013165862A1 GEARED TURBOFAN WITH THREE TURBINES ALL CO-ROTATING 审中-公开
标题翻译：具有三轮涡轮机的所有旋转齿轮
公开(公告)号：WO2013165862A1
公开(公告)日：2013-11-07
申请号：PCT/US2013/038560
申请日：2013-04-29
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SCHWARZ, Frederick M. , KUPRATIS, Daniel Bernard , PRAISNER, Thomas J.
IPC分类号： F02K3/04
CPC分类号： F02K3/06 , F02C7/36 , F05D2260/40311
摘要： A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction.
摘要翻译：燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。第一涡轮转子驱动第二压缩机转子和第二涡轮转子。第二涡轮驱动压缩机转子。风扇驱动涡轮机位于第二涡轮转子的下游。风扇驱动涡轮驱动风扇通过齿轮减速。第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。第二压缩机转子和第一涡轮转子一起作为高速滑阀。高速滑阀，中速滑阀和风扇驱动涡轮机构造成沿相同的第一方向旋转。

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