公开(公告)号：US12078079B2

公开(公告)日：2024-09-03

申请号：US18296576

申请日：2023-04-06

申请人： IHI CORPORATION

发明人： Yasuhiro Okamura ,  Masaaki Hamabe ,  Daisuke Nishii ,  Juo Furukawa

IPC分类号： F01D5/14

CPC分类号： F01D5/145 ,  F05D2240/304 ,  F05D2250/14

摘要： Provided is a blade capable of optimizing an outflow angle in substantially the entire hub region and tip region, particularly in a blade-end-side hub region and a blade-end-side tip region. The blade includes: a base blade part; a suction-side elevated portion provided on a suction surface near a trailing edge in at least one of the blade-end-side tip region and the blade-end-side hub region of the base blade part; and a pressure-side elevated portion provided on a pressure surface near the trailing edge in at least one of a midspan-side tip region and a midspan-side hub region of the base blade part. An airfoil at each spanwise position where the elevated portion is provided is such that a trailing-edge curve of a base airfoil is changed to a modified trailing-edge curve. The modified trailing-edge curve includes a portion of the trailing-edge curve of the base airfoil in the spanwise region where the elevated portion is provided, the portion being closer to the pressure side or the suction side than the trailing edge, and an elevated portion curve. The elevated portion curve includes a concave front-side curve and a convex rear-side curve.

公开(公告)号：US20240117743A1

公开(公告)日：2024-04-11

申请号：US17960230

申请日：2022-10-05

申请人： GENERAL ELECTRIC COMPANY

发明人： Brian Kenneth Corsetti ,  John Curtis Calhoun ,  Dane Michael Dale

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2240/307 ,  F05D2250/14 ,  F05D2250/38 ,  F05D2260/2214

摘要： An apparatus for an engine component in a turbine engine. The engine component including a wall with a cooling hole having a passage extending between an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface. The cooling hole including a layup surface defining a first angle (α) and a layback surface defining a second angle (β).

公开(公告)号：US20180016987A1

公开(公告)日：2018-01-18

申请号：US15553207

申请日：2015-03-10

申请人： GENERAL ELECTRIC COMPANY ,  MIDDLE RIVER AIRCRAFT SYSTEMS

发明人： Graham Frank Howarth ,  Andrew Michael Roach ,  Steven Thomas Davies ,  Richard David Cedar ,  Michael Moses Martinez ,  Timothy Richard DePuy

IPC分类号： F02C7/24

CPC分类号： F02C7/24 ,  F02C7/045 ,  F02K1/827 ,  F05D2220/323 ,  F05D2250/11 ,  F05D2250/14 ,  F05D2250/283 ,  F05D2260/963 ,  G10K11/172 ,  Y02T50/672

摘要： An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and closes the open faces, a set of perforations located in the facing sheet and in fluid communication with a corresponding one of the cavities to form a set of acoustic resonators, and at least a subset of the perforations have an axially-oriented, relative to the axial flow path, inlet.

公开(公告)号：US09869201B2

公开(公告)日：2018-01-16

申请号：US14725004

申请日：2015-05-29

申请人： GENERAL ELECTRIC COMPANY

发明人： Thomas Earl Dyson ,  Victor John Morgan ,  Neelesh Nandkumar Sarawate ,  David Benjamin Helmer

IPC分类号： F01D9/02 ,  F01D11/00 ,  F01D25/12

CPC分类号： F01D25/12 ,  F01D11/005 ,  F05D2250/14 ,  F05D2260/201 ,  Y02T50/676

摘要： The present application provides a seal for use between adjacent turbine components and with a cooling flow. The seal may include an impingement baffle top plate, a base plate, and one or more spacer elements therebetween. The cooling flow provides cooling through the impingement baffle top plate.

公开(公告)号：US09816388B1

公开(公告)日：2017-11-14

申请号：US15272864

申请日：2016-09-22

申请人： General Electric Company

发明人： Kevin Richard Kirtley ,  Ibrahim Sezer ,  Benjamin P. Lacy

IPC分类号： F01D11/08 ,  F01D11/02 ,  F16J15/447 ,  B33Y80/00

CPC分类号： F01D11/02 ,  B22F3/1055 ,  B22F5/009 ,  B33Y80/00 ,  F01D11/127 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/31 ,  F05D2250/121 ,  F05D2250/132 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/283 ,  F05D2260/20 ,  F05D2300/514 ,  F16J15/447

摘要： A seal in a gas turbine engine includes a shim base and a honeycomb structure having a number of cavities are formed as a single unitary structure using additive manufacturing.

公开(公告)号：US09810178B2

公开(公告)日：2017-11-07

申请号：US14818596

申请日：2015-08-05

申请人： General Electric Company

发明人： Mustafa Dindar ,  Scott Andrew Burton ,  Keith Edward James Blodgett ,  Richard David Cedar

IPC分类号： F02K1/78 ,  F02K3/06 ,  F01D25/24 ,  F02K1/09 ,  F02K1/00 ,  F02K1/06 ,  F02K1/08

CPC分类号： F02K1/78 ,  F01D25/24 ,  F01D25/30 ,  F02K1/00 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K3/06 ,  F05D2250/14

摘要： A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.

公开(公告)号：US09726189B2

公开(公告)日：2017-08-08

申请号：US13993275

申请日：2012-02-13

申请人： Hideaki Nishida ,  Keitaro Kamata ,  Isao Tomita ,  Takashi Shiraishi ,  Noriyuki Hayashi ,  Motoki Ebisu ,  Hiroshi Suzuki ,  Hiroshi Ogita

发明人： Hideaki Nishida ,  Keitaro Kamata ,  Isao Tomita ,  Takashi Shiraishi ,  Noriyuki Hayashi ,  Motoki Ebisu ,  Hiroshi Suzuki ,  Hiroshi Ogita

IPC分类号： F04D29/05 ,  F04D29/056 ,  F16C17/18 ,  F16C43/02 ,  F16C33/10 ,  F01D25/16 ,  F01D1/24 ,  F01D25/18 ,  F16C17/02 ,  F16C17/26 ,  F16C33/14

CPC分类号： F04D29/056 ,  F01D1/24 ,  F01D25/16 ,  F01D25/162 ,  F01D25/166 ,  F01D25/186 ,  F05D2220/40 ,  F05D2250/14 ,  F05D2250/70 ,  F05D2260/96 ,  F16C17/028 ,  F16C17/18 ,  F16C17/26 ,  F16C33/1075 ,  F16C33/14 ,  F16C43/02 ,  F16C2220/40 ,  F16C2220/60 ,  F16C2220/70 ,  F16C2360/24 ,  Y10T29/49668

摘要： A turbocharger and a method of manufacturing a floating bush with which noise can be reduced, and the rotation speed can be increased. In a turbocharger in which a rotating shaft having a circular cross-section and connecting a turbine rotor and a compressor rotor is supported in a freely rotatable manner, at two axially separated positions via floating bushes, by an inner circumferential surface disposed so as to surround the rotating shaft in a bearing housing, an inner circumferential surface of each of the floating bushes has a non-circular shape in which the curvature of the cross-sectional shape varies in the circumferential direction.

公开(公告)号：US09714582B2

公开(公告)日：2017-07-25

申请号：US14286754

申请日：2014-05-23

申请人： SOLAR TURBINES INCORPORATED

发明人： Rodolfo G. Alonte ,  Bruno Enriquez Struck

IPC分类号： F01D21/00 ,  G01K7/02 ,  G01M15/14 ,  F01D17/08 ,  G01K13/02 ,  G01K1/08

CPC分类号： F01D21/003 ,  F01D17/085 ,  F05D2250/14 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2250/241 ,  G01K1/08 ,  G01K7/023 ,  G01K13/02 ,  G01K2013/024 ,  G01M15/14

摘要： A sensor assembly for a gas turbine engine is disclosed. The sensor assembly includes a bushing and a probe. The probe includes a body, an anti-vortex tip, and a tip end. The body extends from the bushing and includes a body surface. The body surface is a right circular cylinder with a first diameter. The anti-vortex tip extends from the body and includes an anti-vortex tip surface. The anti-vortex tip surface is a conical surface extending from the body surface to a second diameter at a taper angle from fourteen degrees to sixteen degrees. The tip end extends with a spherical shape from the anti-vortex tip.

公开(公告)号：US20170037813A1

公开(公告)日：2017-02-09

申请号：US14818596

申请日：2015-08-05

申请人： General Electric Company

发明人： Mustafa DINDAR ,  Scott Andrew BURTON ,  Keith Edward James BLODGETT ,  Richard David CEDAR

IPC分类号： F02K1/78 ,  F02K3/06 ,  F01D25/24 ,  F02C3/04

CPC分类号： F02K1/78 ,  F01D25/24 ,  F01D25/30 ,  F02K1/00 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K3/06 ,  F05D2250/14

摘要： A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.

摘要翻译： 涡轮风扇排气喷嘴包括：圆锥形内壳，同轴地设置在周围的外壳内，以限定其间的环形流动管道，其终止于外壳的后缘处的出口，并且内壳终止于出口后部的后缘; 以及托架，其周向地中断所述管道，其中所述外壳的后缘的至少一部分是垂直非共面的。

公开(公告)号：US20160237827A1

公开(公告)日：2016-08-18

申请号：US15139379

申请日：2016-04-27

申请人： Siemens Energy, Inc.

发明人： Christian Xavier Campbell ,  Anand A. Kulkarni ,  Daniel M. Eshak ,  Allister William James ,  Phillip Behling ,  Ahmed Kamel

IPC分类号： F01D5/14 ,  B22F3/105 ,  B22F5/04 ,  B23K26/342

CPC分类号： F01D5/147 ,  B22D19/10 ,  B22F3/1055 ,  B22F5/04 ,  B22F2003/1058 ,  B22F2007/068 ,  B23K26/342 ,  B23K2101/001 ,  B23P15/04 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/005 ,  F01D5/20 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2240/307 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/14 ,  Y02P10/295

摘要： A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings (80) defining the wall corrugations may be semi-circular, rectangular, trapezoidal, or elliptical in cross-sectional shape. The resulting blade has lower tip mass while retaining adequate mechanical properties. The tip portion may be formed to have a directionally solidified grain structure on a base portion having an equiaxed grain structure.

摘要翻译： 一种燃气涡轮发动机叶片（10），包括具有铸造壁的基部（12）和附接到基部的顶端部分（14），并具有通过添加剂制造工艺形成的壁（60）。 尖端部分壁可以形成为固体并且厚度小于2mm，或者其可以是波纹状，并且厚度大于2mm。 限定壁波纹的开口（80）可以是横截面形状的半圆形，矩形，梯形或椭圆形。 所得到的刀片具有较低的尖端质量，同时保持足够的机械性能。 尖端部分可以形成为在具有等轴晶粒结构的基部上具有定向凝固的晶粒结构。