公开(公告)号：US20240360764A1

公开(公告)日：2024-10-31

申请号：US18671288

申请日：2024-05-22

Applicant: Hamilton Sundstrand Corporation

Inventor： Viktor Kilchyk ,  Brent Merritt

IPC: F01D5/02 ,  F01D11/02

CPC classification number: F01D5/02 ,  F01D11/02 ,  F05D2300/603

Abstract: An impeller includes a hub. The hub has a first end and a second end and includes an impeller disk at the second end of the hub. The impeller disk includes a first annular protrusion extending from the impeller disk. A first pocket is in a radially outer side of the first annular protrusion. The impeller also includes a first preloading band positioned in the first pocket. The first preloading band encircles the radially outer side of the first annular protrusion. The impeller also includes blades connecting to a radially outer surface of the hub.

公开(公告)号：US20240191722A1

公开(公告)日：2024-06-13

申请号：US18554573

申请日：2021-04-19

Applicant: CLIMAT GESTION SA

Inventor： Jürg SCHIFFMANN ,  Luis Eric OLMEDO

IPC: F04D29/053 ,  F01D5/02 ,  F04D29/26

CPC classification number: F04D29/053 ,  F01D5/02 ,  F04D29/26 ,  F05D2220/30 ,  F05D2240/24

Abstract: Disclosed is a turbocompressor including at least one rotor the axis of which includes at least one preloading element permanently maintaining the diameter of the axis larger than its natural diameter. Also disclosed is a high speed rotor and a method of manufacturing the same.

公开(公告)号：US20240084737A1

公开(公告)日：2024-03-14

申请号：US18510848

申请日：2023-11-16

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F02C7/32 ,  F01D5/02 ,  F01D25/34

CPC classification number: F02C7/32 ,  F01D5/02 ,  F01D25/34 ,  F05D2220/32 ,  F05D2240/20 ,  F05D2260/941

Abstract: A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.

公开(公告)号：US20230396107A1

公开(公告)日：2023-12-07

申请号：US18184764

申请日：2023-03-16

Applicant: GE AVIATION SYSTEMS LLC

Inventor： Balamurugan Sridharan ,  Hari Meka ,  Mamatha Ramakrishnaiah

IPC: H02K1/32 ,  H02K7/18 ,  H02K9/19 ,  H02K11/04 ,  F01D5/02

CPC classification number: H02K1/32 ,  H02K7/1823 ,  H02K9/19 ,  H02K11/04 ,  F01D5/02 ,  F05D2220/32

Abstract: A rotor assembly for an electric machine includes a first end and a second end, the second end distal from the first end in an axial direction, a first radial wall extending between the first end and the second end and defining an inner cavity, and a second radial wall extending between the first end and the second end, the second radial wall radially-overlying the first radial wall and defining an outer cavity between the first radial wall and the second radial wall.

公开(公告)号：US11834963B2

公开(公告)日：2023-12-05

申请号：US17672107

申请日：2022-02-15

Applicant: Raytheon Technologies Corporation

Inventor： Mark T. Ucasz

IPC: F01D5/28 ,  C23C30/00 ,  C23C28/04 ,  C23C28/00 ,  C23C28/02 ,  F01D25/00 ,  F01D5/02 ,  F01D9/04 ,  F01D1/08 ,  F01D11/08

CPC classification number: F01D5/288 ,  C23C28/028 ,  C23C28/048 ,  C23C28/3215 ,  C23C28/345 ,  C23C30/00 ,  F01D1/08 ,  F01D5/02 ,  F01D9/041 ,  F01D25/007 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2260/95 ,  F05D2300/171 ,  F05D2300/177 ,  F05D2300/611 ,  Y02T50/60

Abstract: A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.

公开(公告)号：US11821371B1

公开(公告)日：2023-11-21

申请号：US17816018

申请日：2022-07-29

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F02C7/32 ,  F01D25/34 ,  F01D5/02

CPC classification number: F02C7/32 ,  F01D5/02 ,  F01D25/34 ,  F05D2220/32 ,  F05D2240/20 ,  F05D2260/941

Abstract: A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.

公开(公告)号：US11806939B2

公开(公告)日：2023-11-07

申请号：US17503880

申请日：2021-10-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lawrence Binek ,  Matthew B. Kennedy ,  Evan Butcher ,  Jesse R. Boyer ,  Vijay Narayan Jagdale ,  Dmytro Mykolayovych Voytovych

IPC: B29C64/40 ,  B29C64/153 ,  F01D5/02 ,  F01D21/04 ,  B33Y30/00 ,  B33Y80/00 ,  B33Y10/00

CPC classification number: B29C64/40 ,  B29C64/153 ,  F01D5/02 ,  F01D21/045 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y80/00 ,  F05D2230/22 ,  F05D2230/233

Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

公开(公告)号：US20230332614A1

公开(公告)日：2023-10-19

申请号：US18006734

申请日：2021-08-24

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： Martin Reimann ,  Kevin Miny

IPC: F04D29/26 ,  F04D29/053 ,  F04D17/12 ,  F04D29/08 ,  F01D5/02 ,  F01D11/00 ,  F16D1/076

CPC classification number: F04D29/266 ,  F04D29/053 ,  F04D17/122 ,  F04D29/083 ,  F01D5/02 ,  F01D11/005 ,  F16D1/076

Abstract: A compressor rotor for turbomachinery, such as a centrifugal compressor, is provided. Disclosed embodiments benefit from a seal assembly including one or more seal members positioned within a Hirth coupling to inhibit passage of process fluid being processed by the compressor. A circumferentially extending groove is arranged in a toothed meshing interface of the Hirth coupling to receive and securely hold the one or more seal members within the Hirth coupling. The groove may be configured with features, such as may define a dovetail groove, to facilitate assembly of certain seal members into the groove. Disclosed embodiments can make use of any of various sealing modalities for the seal member within the Hirth coupling based on the needs of a given application.

公开(公告)号：US20230323836A1

公开(公告)日：2023-10-12

申请号：US17716523

申请日：2022-04-08

Applicant: Raytheon Technologies Corporation

Inventor： Paul R. Adams ,  Frederick M. Schwarz ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Gabriel L. Suciu

IPC: F02K3/06 ,  F02C7/36

CPC classification number: F02K3/06 ,  F02C7/36 ,  F01D5/02

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US11754094B2

公开(公告)日：2023-09-12

申请号：US17689260

申请日：2022-03-08

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： David A. Topol

IPC: F04D29/66 ,  F01D5/26 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D25/04 ,  F04D29/32 ,  F04D29/54

CPC classification number: F04D29/661 ,  F01D5/02 ,  F01D5/12 ,  F01D5/26 ,  F01D9/041 ,  F01D25/04 ,  F04D29/324 ,  F04D29/544 ,  F04D29/66 ,  F04D29/663 ,  F04D29/666 ,  F05D2260/96 ,  Y02T50/60

Abstract: A gas turbine engine according to an aspect of the present disclosure includes, among other things, a propulsor section, a compressor section including a first compressor and a second compressor, and a turbine section including a first turbine and a second turbine. The first compressor includes a plurality of arrays of airfoils defining a plurality of compressor stages. A number of airfoils in each downstream array of the plurality of arrays is a factor (F) of a number of airfoils in a respective immediately upstream array of the plurality of arrays. The factor (F) is between 1.19 and 1.55 for each of the downstream arrays of the first compressor.