公开(公告)号：US20240183359A1

公开(公告)日：2024-06-06

申请号：US18075159

申请日：2022-12-05

Applicant: Hamilton Sundstrand Corporation

Inventor： Zhongtao Dai ,  Ram Ranjan ,  Kathryn L. Kirsch

IPC: F04D25/08 ,  F04D29/32 ,  F04D29/58

CPC classification number: F04D25/082 ,  F04D29/321 ,  F04D29/5806

Abstract: A ram air fan inlet assembly for cabin air compressor (CAC) motor cooling flow enhancement includes a gas path defined by a ram air duct and a fan section, a CAC motor cooling return duct having an outlet provided through a wall of the ram air duct, and a centerbody body disposed in the ram air duct. The fan section is disposed immediately downstream and abutting the ram air duct. The ram air duct and fan section share a common axis. The centerbody is disposed about the common axis and configured to reduce of volume of the gas flow path in the ram air duct. The centerbody and the outlet axially overlap.

公开(公告)号：US11982282B2

公开(公告)日：2024-05-14

申请号：US18097953

申请日：2023-01-17

Applicant: Zhenkun Wang

Inventor： Zhenkun Wang

IPC: F04D25/08 ,  F04D25/02 ,  F04D25/06 ,  F04D29/32 ,  F04D29/54

CPC classification number: F04D25/08 ,  F04D25/02 ,  F04D25/06 ,  F04D29/321 ,  F04D29/545

Abstract: An energy-saving device for rapidly and infinitely compressing air includes housing, rotating shaft, spiral fan blade, power unit, transmission gear set, and fixing bracket, it is characterized in that the housing is connected with the fixing bracket, the rotating shaft with the spiral fan blade has upper and lower transmission gear sets, the power unit provided on the fixing bracket rotates the rotating shaft through the transmission gear set, so that a tornado-like airflow is generated in the space between the housing and rotating shaft, the devices can be stacked infinitely, so that the airflow is continuously accelerated to produce a powerful air thrust. The present invention can be widely used in aircraft and other vehicles, weapons, and protection and other aspects.

公开(公告)号：US20240026888A1

公开(公告)日：2024-01-25

申请号：US18044815

申请日：2021-10-01

Applicant: Edwards Japan Limited

Inventor： Tooru Miwata ,  Yoshiyuki Sakaguchi ,  Yoshiyuki Takai ,  Yasuhiro Shibata

IPC: F04D19/04 ,  F04D29/32

CPC classification number: F04D19/042 ,  F04D29/321 ,  F05D2250/292

Abstract: A lower portion of a cylindrical portion provided in a vacuum pump on the outlet port side has an extension portion extending to a further downstream side than a stationary part of a thread groove exhaust element. In the extension portion, the smaller the outer diameter, the smaller the stress applied to the inner diameter side during rotation. As such, the configuration including a reduced diameter portion reduces the stress applied to the inner diameter side of the cylindrical portion without lowering the rotation speed of the rotating body. Additionally, providing a gradually decreasing diameter structure in the extension portion reduces stress concentration at the reduced diameter portion.

公开(公告)号：US20230332622A1

公开(公告)日：2023-10-19

申请号：US18207805

申请日：2023-06-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F04D25/04 ,  F04D29/32 ,  F04D29/68 ,  F04D29/54 ,  F04D29/52 ,  F04D19/02 ,  F04D29/56 ,  F02K3/04

CPC classification number: F04D29/547 ,  F02K3/04 ,  F02K3/06 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/681 ,  F05D2220/3217 ,  F05D2220/36 ,  F05D2260/606

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor that delivers flow to a core flowpath and a compressor section including first and second compressors. The core flowpath passes through the first compressor. The core flowpath in the first compressor has an outer diameter relative to the engine longitudinal axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US20230220799A1

公开(公告)日：2023-07-13

申请号：US17663308

申请日：2022-05-13

Applicant: General Electric Company

Inventor： Kudum Shinde ,  Ravindra Shankar Ganiger

IPC: F02C3/04 ,  F04D29/32 ,  F02C7/18 ,  F02C7/36 ,  F02C7/32

CPC classification number: F02C3/04 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36 ,  F04D29/321 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60

Abstract: A gas turbine engine includes a compressor section with a compressor rotor shaft assembly including a plurality of compressor rotors longitudinally spaced apart from each other via respective ones of a plurality of shaft sections of a rotor shaft, each compressor rotor of the plurality of compressor rotors having a plurality of rotor vanes extending radially outward therefrom and being circumferentially spaced about the compressor rotor. A stator shroud assembly has a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing. A pressurized air source generates a flow of pressurized air to be provided to the compressor section, and a plurality of pressurized airflow nozzles are connected with the pressurized air source and provide the flow of pressurized air into the compressor flow passage to cause the compressor rotor shaft assembly to rotate.

公开(公告)号：US20230193830A1

公开(公告)日：2023-06-22

申请号：US18110454

申请日：2023-02-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D25/16 ,  F01D5/06 ,  F02C3/06 ,  F02C7/06 ,  F04D29/32

CPC classification number: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D25/162 ,  F01D5/06 ,  F02C3/06 ,  F02C7/06 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A gas turbine engine includes a compressor section including a first compressor, a turbine section including a first turbine and a second turbine, a first shaft and a second shaft, the first shaft interconnecting the first turbine and the second compressor, and a geared architecture. The first shaft is supported on a first bearing in an overhung manner. A performance ratio is between 0.5 and 1.5.

公开(公告)号：US20190242393A1

公开(公告)日：2019-08-08

申请号：US16211663

申请日：2018-12-06

Applicant: Miba Sinter Austria GmbH

Inventor： Gerold STETINA ,  Christian SANDNER ,  Thomas RIEDL ,  Dietmar ANDESSNER

IPC: F04D29/041 ,  F04D3/00 ,  F04D15/00 ,  F04D19/00 ,  F04D25/02 ,  F04D25/06 ,  F04D29/18 ,  F04D29/32 ,  H02K7/14 ,  H02K16/02 ,  H02K21/24 ,  F25B31/02

CPC classification number: F04D29/041 ,  F04D3/00 ,  F04D15/0066 ,  F04D19/007 ,  F04D25/026 ,  F04D25/068 ,  F04D29/185 ,  F04D29/321 ,  F25B31/026 ,  H02K7/14 ,  H02K16/02 ,  H02K21/24

Abstract: A pump arrangement includes an axial-flow machine and a drive to convey fluid mounted in a housing. The axial-flow machine is formed by at least one first rotor having permanent magnets, a shaft connected to the first rotor and a stator arrangement with stator teeth distributed concentrically around the shaft axis circumferentially and axially separated from the first rotor by an air gap. The stator teeth have axially-opposite end portions and a tooth core therebetween wound with at least one coil winding. The second end portion, turned away from the first rotor, of each stator tooth forms a tooth root joined to a back plate. The first rotor is an eccentric disk and on the side away from the stator arrangement has an eccentric cam, radially spaced from the shaft axis, and rotatably and torque-transmittingly connected to the drive. An axial-flow machine and a compressor includes the pump arrangement.

公开(公告)号：US10077662B2

公开(公告)日：2018-09-18

申请号：US14904500

申请日：2014-07-01

Applicant: Siemens Aktiengesellschaft

Inventor： Karsten Kolk ,  Peter Schröder ,  Vyacheslav Veitsman

IPC: F01D5/06 ,  F01D5/08 ,  F04D29/32 ,  F01D5/14

CPC classification number: F01D5/06 ,  F01D5/087 ,  F01D5/147 ,  F04D29/321 ,  Y02T50/673 ,  Y02T50/676

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is designed to conduct a medium, such as compressor air, in the interior of the gas turbine. In order to conduct the medium in the interior with low flow losses and at the same time to specify a rotor that can be produced comparatively simply and economically, a separately produced blade wheel is arranged between the mutually adjacent hub regions of the two rotor discs. The first side of said blade wheel lies against the hub region of the second rotor disc and the second side opposite the first side has a number of ribs, which extend from radially outside to radially inside.

公开(公告)号：US20180209427A1

公开(公告)日：2018-07-26

申请号：US15747178

申请日：2016-07-22

Applicant: Nuovo Pignone Tecnologie Srl

Inventor： Giuseppe IURISCI ,  Simone CORBO ,  Giuseppe SASSANELLI

IPC: F04D17/02 ,  F04D25/16 ,  F04D25/02 ,  F04D29/28 ,  F04D29/32 ,  F04D29/52 ,  F04D17/12 ,  F04D19/02 ,  F25J1/00 ,  F25J1/02

CPC classification number: F04D17/025 ,  F04D17/12 ,  F04D19/028 ,  F04D25/02 ,  F04D25/16 ,  F04D27/023 ,  F04D27/0238 ,  F04D27/0269 ,  F04D29/286 ,  F04D29/321 ,  F04D29/522 ,  F25J1/0022 ,  F25J1/004 ,  F25J1/0052 ,  F25J1/0055 ,  F25J1/0072 ,  F25J1/0082 ,  F25J1/0085 ,  F25J1/0087 ,  F25J1/0207 ,  F25J1/021 ,  F25J1/0216 ,  F25J1/0218 ,  F25J1/0279

Abstract: The LNG plant comprises a compression train and a further compression. The compression train (100) comprises comprising an engine and a compressor driven by the engine; the compressor is an axial compressor and comprises a first set of axial compression stages and a second set of axial compression stages arranged downstream the first set of axial compression stages; at least the first set and the second set of axial compression stages are housed inside one case. The further compression train comprises a further engine and a further compressor driven by the further engine; the further compressor is a centrifugal compressor and comprises a first set of impellers and a second set of impellers arranged downstream or upstream the first set of impellers.

公开(公告)号：US20180209280A1

公开(公告)日：2018-07-26

申请号：US15877839

申请日：2018-01-23

Applicant: ROLLS-ROYCE plc

Inventor： John P E FORSDIKE ,  Simon E. BRAY ,  Gavin J. BAXTER ,  Andrew R. WALPOLE

IPC: F01D5/30 ,  F01D5/02 ,  B23K20/12

CPC classification number: F01D5/3061 ,  B23K15/0086 ,  B23K15/0093 ,  B23K20/1205 ,  B23K20/129 ,  B23K20/16 ,  B23K20/233 ,  B23K20/24 ,  B23K26/0006 ,  B23K26/34 ,  B23K2101/001 ,  B23K2103/08 ,  B23K2103/26 ,  B33Y80/00 ,  F01D5/02 ,  F01D5/34 ,  F04D29/321 ,  F04D29/322 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/233 ,  F05D2230/239 ,  F05D2230/30 ,  F05D2300/175 ,  F05D2300/606

Abstract: A method (56) for fabricating an integral assembly (24) is disclosed. The method comprises providing (56) a first workpiece (26) having a first surface and a second workpiece (30) having a second surface (54), performing a first bonding process between the first surface of the first workpiece (26) and the second surface (54) of the second workpiece (30) the bulk material of the first workpiece having a friction weld property that makes it more difficult to weld than a friction weld property at the surface.