公开(公告)号：US20240254942A1

公开(公告)日：2024-08-01

申请号：US18593232

申请日：2024-03-01

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：US11879390B2

公开(公告)日：2024-01-23

申请号：US17432853

申请日：2020-02-25

申请人： SAFRAN NACELLES

发明人： Thierry Jacques Albert Le Docte

IPC分类号： F02C7/047 ,  B64C7/02 ,  B64D15/04

CPC分类号： F02C7/047 ,  B64C7/02 ,  B64D15/04 ,  F05D2220/323 ,  F05D2250/25 ,  F05D2250/323 ,  F05D2250/73 ,  F05D2260/2212

摘要： The invention relates to a de-icing device for an air intake of an aircraft turbojet engine nacelle extending along an X-axis in which an air stream flows from upstream to downstream, the air intake having an inner cavity, extending annularly about the X-axis, which comprises an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the walls being connected by a leading edge, the de-icing device comprising at least one injector for injecting a stream of hot air into the inner cavity, the injector comprising a nozzle extending along a nozzle axis, the nozzle being configured to inject a stream of hot air having a dissymmetry along the nozzle axis.

公开(公告)号：US20190048933A1

公开(公告)日：2019-02-14

申请号：US16078243

申请日：2016-03-01

申请人： MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.

发明人： Yuya KOJIMA ,  Tatsuya ISHIZAKI ,  Yosuke DAMMOTO ,  Yoji AKIYAMA

IPC分类号： F16C33/10

CPC分类号： F16C33/1045 ,  F01D25/164 ,  F01D25/166 ,  F01D25/186 ,  F01M1/18 ,  F01M2011/0033 ,  F01M2011/021 ,  F05D2220/40 ,  F05D2250/15 ,  F05D2250/73 ,  F05D2260/609 ,  F16C17/02 ,  F16C17/18 ,  F16C17/26 ,  F16C33/106 ,  F16C2360/24

摘要： The present invention improves the drainability of lubricating oil. The present invention comprises: a rotating shaft (14); a journal bearing that is provided to the rotating shaft (14) and rotationally supports the rotating shaft (14); a bearing housing part that houses the journal bearing; and a drain oil space chamber (47) that acts as an oil drainage passage that communicates with the bearing housing part, is provided along the periphery of the rotating shaft (14), and is formed to open downward. Within a region that is in and above a horizontal plane H that passes through the center of the rotating shaft (14), the smallest cross-sectional area of the oil drainage passage in a radial-direction cross-section thereof is on the anterior side in the rotational direction of the rotating shaft (14) with respect to a vertical plane P that passes though the center (O) of the rotating shaft (14), and the largest cross-sectional area of the oil drainage passage in the radial-direction cross-section is on the posterior side in the rotational direction of the rotating shaft (14) with respect to the vertical plane that passes through the center (O) of the rotating shaft (14).

公开(公告)号：US20180258778A1

公开(公告)日：2018-09-13

申请号：US15571139

申请日：2015-08-28

申请人： SIEMENS AKTIENGESELLSCHAFT

发明人： Jacob William Hardes ,  Manish Kumar ,  Timothy A. Fox

IPC分类号： F01D9/02 ,  F02C3/14

CPC分类号： F01D9/023 ,  F02C3/14 ,  F05D2240/35 ,  F05D2250/73

摘要： A gas turbine engine has a non-axially symmetric main duct portion (113). The non-axially symmetric main duct portion (113) may provide improved aerodynamics, heat load, structural strength and engine compactness.

公开(公告)号：US10060390B2

公开(公告)日：2018-08-28

申请号：US13407805

申请日：2012-02-29

申请人： Steven H. Zysman ,  Edward F. Migliaro, Jr.

发明人： Steven H. Zysman ,  Edward F. Migliaro, Jr.

IPC分类号： F02K1/72 ,  F02K1/76

CPC分类号： F02K1/72 ,  F02K1/763 ,  F05D2250/73 ,  F05D2260/50 ,  Y10T29/49234

摘要： A gas turbine engine includes an engine core outer casing and a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct. A plurality of drag links is used to pivot blocker doors into a flow blocking position in the bypass duct when a thrust reverser is deployed. The plurality of drag links is located within the bypass duct in an area of non-uniform flow defined by a plurality of local airflow angles. Each drag link is individually configured to align with one of the local flow angles.

公开(公告)号：US20180142695A1

公开(公告)日：2018-05-24

申请号：US15874957

申请日：2018-01-19

申请人： IHI Corporation

发明人： Hiroshi TOMARU

IPC分类号： F04D29/18 ,  F04D3/02

CPC分类号： F04D29/181 ,  F04D1/025 ,  F04D3/02 ,  F04D7/00 ,  F05D2240/303 ,  F05D2250/292 ,  F05D2250/73

摘要： An inducer includes a hub and a blade which radially protrudes from the hub and is helically provided. The inducer has a thick portion in which a first distance and a second distance coincides with each other in a region outside a position at which a height ratio of the blade is 0.5 while the first distance is shorter than the second distance in a region inside the position at which the height ratio of the blade is 0.5, in which the height ratio is a ratio of a distance from a connection portion between the hub and a root portion of the blade with respect to a height of the blade which is a distance from the connection portion between the hub and the root portion of the blade to a tip portion of the blade in the radial direction of the blade.

公开(公告)号：US09932988B2

公开(公告)日：2018-04-03

申请号：US14107660

申请日：2013-12-16

申请人： United Technologies Corporation

发明人： David Maliniak ,  Nathan F. Champion ,  Kenneth A. Frisk

IPC分类号： F01D17/14 ,  F01D17/16 ,  F04D29/56

CPC分类号： F04D29/563 ,  F01D17/162 ,  F05D2250/14 ,  F05D2250/73

摘要： A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.

公开(公告)号：US09909530B2

公开(公告)日：2018-03-06

申请号：US14295566

申请日：2014-06-04

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Thomas G Tillman ,  Wesley K. Lord

IPC分类号： F02K1/52 ,  B64D29/04 ,  F02K1/12 ,  F02K3/06 ,  F02K1/00

CPC分类号： F02K1/52 ,  B64D29/04 ,  F02K1/002 ,  F02K1/12 ,  F02K3/06 ,  F05D2220/36 ,  F05D2250/73

摘要： A fan section for an engine has a fan which rotates about an axis, the fan has an inlet for ingesting ambient air, and a non-axisymmetric nozzle for providing the fan with non-uniform back pressure.

公开(公告)号：US20170312869A1

公开(公告)日：2017-11-02

申请号：US15652871

申请日：2017-07-18

申请人： Dynamic Metals, LLC

发明人： Bill Buitenhuis ,  Jack Opielka

IPC分类号： B23P15/00 ,  B21F37/00 ,  B21D5/08 ,  B21D53/20

CPC分类号： B23P15/00 ,  B21D5/08 ,  B21D53/20 ,  B21F37/00 ,  F01D11/005 ,  F05D2220/32 ,  F05D2230/26 ,  F05D2240/55 ,  F05D2250/73 ,  F05D2250/75 ,  F16J15/0887

摘要： A process of forming a turbine engine seal includes the steps of: providing a flat strip of material; roll forming the flat strip of material forming an asymmetric profile in the flat strip of material; coiling the formed asymmetric profile into an overlapping ring shape; cutting the circular shape to a predetermined length; and joining ends of the predetermined length forming the seal. The seal includes at least two peaks that are formed on opposing sides of a gap. The at least two peaks contact opposing sides of a U shaped profile at a zero radius. The asymmetric profile includes a circular shape and the ends are joined.

公开(公告)号：US20170288504A1

公开(公告)日：2017-10-05

申请号：US15088779

申请日：2016-04-01

申请人： Prestolite Electric, Inc.

发明人： Zoltan Takacs ,  Michael J. Hanchett

IPC分类号： H02K9/06 ,  F04D29/58 ,  F04D29/28 ,  F04D29/42 ,  F04D17/16 ,  F04D25/06

CPC分类号： H02K9/06 ,  F04D17/162 ,  F04D25/06 ,  F04D29/281 ,  F04D29/424 ,  F04D29/5806 ,  F04D29/5813 ,  F05D2250/73 ,  H02K1/243 ,  H02K3/24 ,  H02K5/20 ,  H02K11/046

摘要： Systems and methods are provided for cooling electronics and rear end stator windings in an alternator. The system includes an alternator having a rotor assembly, stator assembly, and dual-sided fan disposed in a housing. The housing includes a drive end, rear end, and sides. The rotor assembly includes drive end and rear end poles. The stator assembly surrounds the poles and includes drive end and rear end stator windings. The dual-sided fan is mounted to the rotor assembly adjacent the rear end poles within the housing. The dual-sided fan includes a separating wall, drive end blade set, and rear end blade set. The drive end blade set extends from a first side of the separating wall and at least partially faces the drive end. The rear end blade set extends from a second side of the separating wall and at least partially faces the rear end.