公开(公告)号：US12071865B2

公开(公告)日：2024-08-27

申请号：US18249838

申请日：2021-10-20

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Christophe Marcel Lucien Perdrigeon ,  Cédric Zaccardi ,  William Henri Joseph Riera

IPC分类号： F01D9/04 ,  F01D25/24

CPC分类号： F01D9/042 ,  F01D25/24 ,  F05D2250/71 ,  F05D2260/30

摘要： A bypass turbomachine is disclosed. The turbomachine includes a longitudinal axis having an upstream blower impeller and a downstream air-flow straightening assembly of a secondary annular passage delimited radially on the inside by a radially inner shroud and radially on the outside by a radially outer shroud, blades extending between the radially inner and outer shrouds and being attached at a first end portion to the radially inner shroud and at a second end portion to the radially outer shroud, the blades including a useful portion extending between the first and second end portions and defining a lower face and an upper face. For each blade, in a plane perpendicular to the longitudinal axis, each aerodynamically useful portion is bent into a C-shape in the circumferential direction.

公开(公告)号：US11952962B1

公开(公告)日：2024-04-09

申请号：US18162269

申请日：2023-01-31

申请人： Pratt & Whitney Canada Corp.

发明人： Eray Akcayoz ,  Mark Cunningham

IPC分类号： F02K1/40

CPC分类号： F02K1/40 ,  F05D2220/323 ,  F05D2250/51 ,  F05D2250/52 ,  F05D2250/71 ,  F05D2250/73

摘要： An exhaust duct of an aircraft engine includes an annular inlet conduit having an inlet central axis, and at least two outlet conduits in flow communication with the inlet conduit. The at least two outlet conduits are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.

公开(公告)号：US20180274381A1

公开(公告)日：2018-09-27

申请号：US15467431

申请日：2017-03-23

申请人： General Electric Company

发明人： Weston Nolan Dooley ,  James Michael Hoffman ,  Gregory Terrence Garay

IPC分类号： F01D11/00 ,  F01D5/30

CPC分类号： F01D11/006 ,  F01D5/30 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2250/71

摘要： A turbine engine component includes: a body bounded by an end face; and a seal slot having an opening communicating with the end face, the seal slot including a receptacle defining a boundary configured to receive and position a spline seal, and an open chamber communicating with the seal slot and extending beyond the boundary.

公开(公告)号：US10036257B2

公开(公告)日：2018-07-31

申请号：US14624666

申请日：2015-02-18

申请人： United Technologies Corporation

发明人： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

IPC分类号： F01D5/14 ,  F01D5/02 ,  F01D15/12 ,  F02C3/14 ,  F02C3/04

CPC分类号： F01D5/141 ,  F01D5/02 ,  F01D15/12 ,  F02C3/04 ,  F02C3/14 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/71 ,  Y02T50/672 ,  Y02T50/673

摘要： An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.

公开(公告)号：US20180202320A1

公开(公告)日：2018-07-19

申请号：US15860133

申请日：2018-01-02

申请人： KABUSHIKI KAISHA TOSHIBA ,  Toshiba Energy Systems & Solutions Corporation

发明人： Hiroaki Mitsui ,  Tsuguhisa Tashima ,  Shogo Iwai ,  Takahiro Ono ,  Daichi Fukabori

IPC分类号： F01D25/30

CPC分类号： F01D25/30 ,  F05D2220/31 ,  F05D2240/14 ,  F05D2250/52 ,  F05D2250/71

摘要： An exhaust hood in an embodiment includes: an outer casing; and an annular diffuser which is provided on a downstream side of a final turbine stage and formed by a cylindrical steam guide and a cylindrical bearing cone provided inside the steam guide. The steam guide includes a curved guide and a flat-plate guide which is provided on a downstream side of the curved guide. When a cross section of the outer casing vertical to the rotation axis of the turbine rotor is viewed from the downstream side of the steam guide, expansion outward in the radial direction of the flat-plate guide is set based on D/H where a distance between the rotation axis of the turbine rotor and an inner surface of the outer casing is H and a distance between the rotation axis of the turbine rotor and a downstream end of the flat-plate guide is D.

公开(公告)号：US20180195403A1

公开(公告)日：2018-07-12

申请号：US15404608

申请日：2017-01-12

申请人： General Electric Company

发明人： Daniel Patrick Kerns ,  Dennis Paul Dry ,  Megan Elizabeth Scheitlin ,  Alexander Martin Sener ,  Jason David Shapiro

IPC分类号： F01D11/10 ,  F01D25/24 ,  F02C7/28 ,  F04D29/52 ,  F04D29/54 ,  F02C3/04 ,  F04D29/64

CPC分类号： F04D29/526 ,  F01D11/08 ,  F01D25/246 ,  F04D29/083 ,  F05D2240/11 ,  F05D2250/411 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2260/36 ,  F05D2300/6033 ,  Y02T50/672

摘要： A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.

公开(公告)号：US20180179901A1

公开(公告)日：2018-06-28

申请号：US15739796

申请日：2015-07-24

申请人： Siemens Aktiengesellschaft

发明人： Nicholas F. Martin, Jr. ,  Andrew S. Lohaus

IPC分类号： F01D5/22 ,  F01D5/14 ,  F01D5/28 ,  F01D11/12

CPC分类号： F01D5/225 ,  F01D5/143 ,  F01D5/147 ,  F01D5/28 ,  F01D11/127 ,  F05D2250/71

摘要： A turbine blade (10) includes a generally elongated airfoil (32) extending span-wise along a radial direction, and a circumferentially extending shroud (70) coupled to a radially outer tip (24) of the airfoil (32). The shroud (70) includes an upstream edge (72) and a downstream edge (74) spaced apart axially. The shroud (70) further includes a radially inner surface (76) adjoining the tip (24) of the airfoil (32) and a radially outer surface (78) generally opposite to the radially inner surface (76). The radially inner surface (76) and the radially outer surface (78) are connected at the upstream edge (72) and at the downstream edge (74). In circumferential cross-section, the shroud (70) has a shape of an aerodynamic lifting body (60, 62) defined by a contour of the radially inner surface (76) and that of the radially outer surface (78). The shape of the aerodynamic lifting body (60, 62) is configured such that a radially inward acting lift force (L) is exerted on the shroud (70) by a generally axial fluid flow (F) over the shroud (70).

公开(公告)号：US09995245B2

公开(公告)日：2018-06-12

申请号：US14396800

申请日：2013-04-26

申请人： GENERAL ELECTRIC COMPANY

发明人： Mustafa Dindar ,  Vaughn Ray Kunze

IPC分类号： F02K1/38 ,  F02K1/46 ,  F02K1/34 ,  F02K1/48 ,  B64D33/04 ,  F02K1/82

CPC分类号： F02K1/386 ,  B64D33/06 ,  B64D2033/045 ,  F02K1/38 ,  F02K1/46 ,  F02K1/48 ,  F02K1/827 ,  F05D2230/20 ,  F05D2230/60 ,  F05D2250/184 ,  F05D2250/61 ,  F05D2250/611 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2260/96 ,  F05D2300/6033 ,  Y02T50/672 ,  Y10T29/49234

摘要： A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end. The plurality of bypass immersion lobes includes a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe has a first crown contour line extending from the forward end to the aft end of the mixer, and the second bypass immersion lobe has a second crown contour line extending from the forward end to the aft end of the mixer. The first crown contour line is different than the second crown contour line.

公开(公告)号：US20180156047A1

公开(公告)日：2018-06-07

申请号：US15872782

申请日：2018-01-16

申请人： SNECMA

发明人： Marco NUCCI ,  Damien MERLOT ,  Jacky RODRIGUEZ

IPC分类号： F01D5/30 ,  F01D5/14

CPC分类号： F01D5/3007 ,  F01D5/141 ,  F01D5/16 ,  F05D2220/3217 ,  F05D2240/12 ,  F05D2250/11 ,  F05D2250/13 ,  F05D2250/294 ,  F05D2250/71 ,  F05D2260/941 ,  F05D2260/96

摘要： The shank of a blade includes a first side and a second side provided with a depression. By concentrating this depression on a single side, a shank that is more rigid and resistant with an equal lightening is obtained, with the stress concentrations depending on the depth of the depression but being absent from first flat side. The vibrations and bending deformations are also reduced.

公开(公告)号：US20180149026A1

公开(公告)日：2018-05-31

申请号：US15365498

申请日：2016-11-30

申请人： Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce High Temperature Composites Inc.

发明人： Daniel K. Vetters ,  Ted J. Freeman ,  Andrew J. Lazur ,  Robert J. Shinavski ,  Wayne S. Steffier

IPC分类号： F01D5/30 ,  F01D5/28 ,  F02C3/04

CPC分类号： F01D5/3015 ,  F01D5/282 ,  F01D5/3007 ,  F01D25/246 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/237 ,  F05D2240/11 ,  F05D2250/185 ,  F05D2250/71 ,  F05D2300/6033 ,  Y02T50/672

摘要： A gas turbine engine includes a turbine having turbine blades and a shroud having a blade track for positioning radially outside of the blades. At least one of the blades and the blade track are secured in place using a dovetail connection between a dovetail receiver and a dovetail assembly formed to include a contoured root.