公开(公告)号：US20160186690A1

公开(公告)日：2016-06-30

申请号：US14911577

申请日：2014-04-17

申请人： United Technologies Corporation

发明人： Razvan Virgil FLOREA ,  Thomas G. TILLMAN ,  William T. COUSINS

IPC分类号： F02K3/06 ,  F02C3/04

CPC分类号： F02K3/06 ,  F01D5/143 ,  F01D5/20 ,  F02C3/04 ,  F02C7/04 ,  F02C7/045 ,  F04D27/0246 ,  F04D29/321 ,  F04D29/526 ,  F04D29/547 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/184 ,  F05D2250/25 ,  F05D2250/294 ,  F05D2250/61 ,  F05D2250/73 ,  F05D2270/102 ,  Y02T50/673

摘要： A gas turbine engine propulsion system and method of assembling such is disclosed. The gas turbine engine propulsion system comprises a gas turbine engine that includes a fan flow path. The fan flow path may extend from the fan inlet to the rear exhaust outlet of the bypass flow path. A portion of the fan flow path, proximal to the fan, is non-axisymmetric. The non-axisymmetric portion may be upstream or downstream of the fan.

摘要翻译： 公开了一种燃气轮机发动机推进系统及其组装方法。 燃气涡轮发动机推进系统包括包括风扇流路的燃气涡轮发动机。 风扇流路可以从旁路流路的风扇入口延伸到后排气口。 靠近风扇的风扇流路的一部分是非轴对称的。 非轴对称部分可以在风扇的上游或下游。

公开(公告)号：US09109455B2

公开(公告)日：2015-08-18

申请号：US13355436

申请日：2012-01-20

申请人： Rohit Chouhan ,  Sumeet Soni ,  Paul Kendall Smith ,  Srinivasa Govardhan Jayana ,  Sylvain Pierre ,  Harish Bommanakatte ,  Santhosh Kumar Vijayan ,  Spencer Aaron Kareff

发明人： Rohit Chouhan ,  Sumeet Soni ,  Paul Kendall Smith ,  Srinivasa Govardhan Jayana ,  Sylvain Pierre ,  Harish Bommanakatte ,  Santhosh Kumar Vijayan ,  Spencer Aaron Kareff

IPC分类号： F01D5/22

CPC分类号： F01D5/225 ,  F01D5/141 ,  F01D5/20 ,  F01D11/02 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2250/20 ,  F05D2250/73 ,  Y02T50/671 ,  Y02T50/673

摘要： Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

摘要翻译： 本公开的实施例涉及包括具有压力侧部分和吸力侧部分的涡轮机叶片梢罩的系统。 压力侧部分和吸力侧部分被涡轮机叶片的平均曲线划分，并且压力侧部分具有比吸力侧部分更大的表面积。

公开(公告)号：US20150063980A1

公开(公告)日：2015-03-05

申请号：US14011698

申请日：2013-08-27

申请人： Honeywell International Inc.

发明人： Vit Houst ,  Daniel Turecek ,  Vaclav Kares ,  Milan Nejedly ,  Michal Mokos ,  Hua Chen ,  Annie Li ,  Michael Zhao ,  Wei Dai ,  Jose Luis Lazaro Bercianos

IPC分类号： F01D5/02

CPC分类号： F01D5/02 ,  F04D17/105 ,  F04D25/024 ,  F04D29/284 ,  F04D29/441 ,  F05D2220/40 ,  F05D2250/73

摘要： A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.

摘要翻译： 双面涡轮增压器压缩机叶轮和形成用于压缩机的扩散器的壳体。 压缩机叶轮的第一侧和第二侧的特征在于装饰和环形区域的不同值。 扩散器的第一侧围绕压缩机叶轮的第一侧，并且扩散器的第二侧围绕压缩机叶轮的第二侧。 扩散器的第一和第二侧的特征在于不同的环面积比。 压缩机叶轮的第一和第二侧的叶片彼此成角度地偏移。 压缩机叶轮被构造成用于通过压缩机叶轮的远离相关涡轮机叶轮的较大流量。

公开(公告)号：US20130302136A1

公开(公告)日：2013-11-14

申请号：US13466254

申请日：2012-05-08

申请人： Eric A. Grover ,  Thomas J. Praisner ,  Joel H. Wagner

发明人： Eric A. Grover ,  Thomas J. Praisner ,  Joel H. Wagner

IPC分类号： F01D11/08

CPC分类号： F01D11/001 ,  F01D5/081 ,  F01D11/02 ,  F05D2250/73 ,  F05D2260/97

摘要： Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces.

摘要翻译： 涡轮机械，例如燃气涡轮发动机，具有相对的第一和第二表面的部件，并且在表面之间具有空腔，并且第一表面相对于第二表面移动。 涡轮机械还具有用于产生并入第一和第二表面的压力变化的至少一个特征。

公开(公告)号：US20130205792A1

公开(公告)日：2013-08-15

申请号：US13544136

申请日：2012-07-09

申请人： Matthew S. Gleiner ,  Atul Kohli ,  Mark F. Zelesky

发明人： Matthew S. Gleiner ,  Atul Kohli ,  Mark F. Zelesky

IPC分类号： F02C7/18 ,  F01D25/12 ,  F04D29/58 ,  F01D5/08

CPC分类号： F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/324 ,  F05D2250/73 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03042 ,  Y02T50/676 ,  Y10T29/49323

摘要： A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.

摘要翻译： 燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 漫射部分包括从计量部分纵向分散的第一凸角和邻近第一凸角的第二凸角并且从计量部分纵向和横向发散。

公开(公告)号：US20130108433A1

公开(公告)日：2013-05-02

申请号：US13286374

申请日：2011-11-01

申请人： Brian Green ,  Sean Nolan

发明人： Brian Green ,  Sean Nolan

IPC分类号： F01D9/04 ,  F01D9/02 ,  F01D5/14

CPC分类号： F01D5/143 ,  F05D2250/73 ,  F05D2250/74 ,  Y02T50/673

摘要： An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.

摘要翻译： 翼型件包括从前缘到后缘轴向延伸的压力和抽吸表面，并且从根部到端部的径向延伸，限定了它们之间的平均间距。 内端壁限定了从根部轴向和周向延伸的内端壁轮廓，并且外端壁限定了从顶端部分轴向和周向延伸的外端壁轮廓。 内外壁轮廓通过从周向均匀的标称内径和外半径变化的径向偏差来限定，其中一个径向偏差沿轴向和周向变化至少为翼型的平均跨度的百分之三。

公开(公告)号：US20130034435A1

公开(公告)日：2013-02-07

申请号：US13196980

申请日：2011-08-03

申请人： Tracy A. Propheter-Hinckley

发明人： Tracy A. Propheter-Hinckley

IPC分类号： F01D9/02 ,  B21D53/00

CPC分类号： F01D9/041 ,  F01D17/162 ,  F05D2250/30 ,  F05D2250/70 ,  F05D2250/73 ,  Y10T29/49229

摘要： A vane assembly for a gas turbine engine includes a first platform, a second platform, and an airfoil that extends radially across an annulus between the first platform and the second platform. The airfoil is centered relative to a centerline axis of the second platform and is offset relative to a centerline axis of the first platform.

摘要翻译： 用于燃气涡轮发动机的叶片组件包括第一平台，第二平台和径向延伸穿过第一平台和第二平台之间的环的翼型件。 翼型件相对于第二平台的中心线轴线居中，并且相对于第一平台的中心线轴线偏移。

公开(公告)号：US11674394B2

公开(公告)日：2023-06-13

申请号：US17173493

申请日：2021-02-11

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Franco Di Paola ,  Julien Lalonde

IPC分类号： F01D5/02 ,  F01D5/06 ,  F01D5/08

CPC分类号： F01D5/022 ,  F01D5/025 ,  F01D5/066 ,  F01D5/087 ,  F05D2240/24 ,  F05D2250/73 ,  F05D2260/4031

摘要： The rotor assembly can have a first disc having a first body extending circumferentially and radially around the axis, a first set of circumferentially distributed blades protruding radially from the first disc, and a male spline extending axially relative the first body, the male spline extending around and along the axis, and a second disc having a second body extending circumferentially and radially around the axis, a second set of circumferentially distributed blades protruding radially from the second disc, and a female spline extending around and along the axis, the female spline receiving the male spline in a spline engagement.

公开(公告)号：US20180347462A1

公开(公告)日：2018-12-06

申请号：US15615152

申请日：2017-06-06

申请人： Raytheon Company

发明人： Nicholas P. Cicchini

IPC分类号： F02C7/04 ,  B64D27/16 ,  B64C30/00 ,  B64C23/04 ,  F02C3/04

CPC分类号： F02C7/04 ,  B64C23/04 ,  B64C30/00 ,  B64D27/16 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/026 ,  F02C3/04 ,  F02K7/10 ,  F05D2220/10 ,  F05D2220/80 ,  F05D2240/35 ,  F05D2250/72 ,  F05D2250/73

摘要： A flight vehicle has a propulsion system that includes an air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes an obstruction that protrudes inwardly from an inner wall of the isolator, into the flow channel in which air flows through the isolator. The obstruction diverts the flow to either side of it. Downstream of the obstruction the flow on either side of the obstruction comes together again, leading to mixing of the flow, for example including mixing of low energy and boundary layer flow with high energy flow. This mixing of flow may make for a more uniform flow at the exit of the isolator. In addition the obstruction may help fix the location of shocks within the isolator, providing longer flow mixing length in the isolator.

公开(公告)号：US20180202391A1

公开(公告)日：2018-07-19

申请号：US15868066

申请日：2018-01-11

申请人： ROLLS-ROYCE plc

发明人： Mark J. WILSON ,  Giulio ZAMBONI

IPC分类号： F02K3/06 ,  F01D9/04 ,  F04D29/54

CPC分类号： F02K3/06 ,  F01D9/041 ,  F02K1/00 ,  F02K3/04 ,  F04D29/542 ,  F04D29/547 ,  F05D2250/184 ,  F05D2250/61 ,  F05D2250/73

摘要： A fan outlet assembly comprises a fan discharge nozzle having a radially inner platform, a radially outer platform arranged coaxially and in radial alignment with the radially inner platform and a circumferential array of outlet guide vanes (110) spanning an annulus defined by the radially inner platform and radially outer platform. An annular duct extends downstream from the circumferential array, the duct having a radially outer wall (112) contiguous with the radially outer platform and a radially inner wall (111) contiguous with the radially inner platform. In a region extending downstream from the circumferential array, the radially inner and outer platforms and/or the radially inner and outer walls having a non-axisymmetric surface bounding the duct. A non-axisymmetric surface may be applied to either or both of the radially outer and radially inner contiguous surfaces and may extend upstream as well as downstream of the circumferential array of outlet guide vanes.