-
公开(公告)号：US12055222B2
公开(公告)日：2024-08-06
申请号：US17956043
申请日：2022-09-29
申请人： John Crane Inc.
发明人： Darin Merrill Rasmussen , Tom Steigerwald , Syed Niamathullah , Dan Kozlowski , James R. Wasser , Michael G. Kalodimos
CPC分类号： F16J15/363 , F16J15/348 , F01D1/00 , F16J15/002 , F16J15/32 , F16J15/38
摘要： A non-collapsible flexible sealing membrane (or bellows) for incorporation in a mechanical seal assembly and use in rotary shaft equipment. The sealing membrane includes a substantially radially outward extending first flange portion, which can be urged into an axially shiftable ring by a biasing mechanism. The sealing membrane further includes a substantially axially outboard extending second coaxial portion, substantially radially inward of the balance diameter of the seal. The horizontal portion is advantageously held fixed to a stub sleeve by an annular band. The angle between the vertical portion and the horizontal portion of sealing membrane enables directional control of the forces acting on stub sleeve and primary ring.
-
公开(公告)号：US12006846B2
公开(公告)日：2024-06-11
申请号：US16759489
申请日：2018-10-31
申请人： MTU Aero Engines AG
发明人： Ralf Homburg , Harsimar Sahota
CPC分类号： F01D9/065 , F05D2230/00
摘要： An intermediate duct (10) for disposition between an outlet of a low-pressure compressor and an inlet of a high-pressure compressor of a turbomachine, in particular of an aircraft engine is provided, the intermediate duct including an outer wall (2) and an inner wall (3) between which are disposed an optional exit stator ring (4) and at least one strut (12) extending radially with respect to a central axis of the intermediate duct (10). The intermediate duct (10) is at least partially manufactured by additive manufacturing. A method for manufacturing such an intermediate duct (10), and a turbomachine having such an intermediate duct (10) are also provided.
-
公开(公告)号：US11946147B2
公开(公告)日：2024-04-02
申请号：US16979971
申请日：2019-02-06
IPC分类号： F01D5/28 , B32B15/04 , C23C4/02 , C23C4/04 , C23C4/134 , C23C28/00 , F01D1/00 , F01D25/00 , F02C7/00
CPC分类号： C23C4/04 , B32B15/04 , C23C4/02 , C23C4/134 , C23C28/30 , C23C28/32 , C23C28/3215 , F01D1/00 , F01D5/28 , F01D5/288 , F01D25/00 , F02C7/00 , B32B2315/02 , C04B2235/3246
摘要： A thermal barrier coating includes a bond coat layer deposited on a substrate, and a ceramic layer deposited on the bond coat layer. The ceramic layer includes a first layer having a porosity of 10% or more and 15% or less, and a second layer having a porosity of 0.5% or more and 9.0% or less and deposited on the first layer.
-
公开(公告)号：US11512378B2
公开(公告)日：2022-11-29
申请号：US17087202
申请日：2020-11-02
申请人： ROLLS-ROYCE plc
发明人： James G. Brewster , Joao P. Martins
摘要： A method of assessing the quality of a bond coat for bonding a ceramic coating to a metallic substrate comprises determining a thresholded summit area for the bond coat.
-
公开(公告)号：US10896512B1
公开(公告)日：2021-01-19
申请号：US16114876
申请日：2018-08-28
发明人： Joseph Rutland , Demian Shaft Raven
IPC分类号： F01D1/00 , G05D1/00 , B64D47/08 , G10K11/178 , B64F5/60 , G06T7/246 , B64D31/06 , B64C39/02 , G08G5/00 , G06T7/73
摘要： An aerial vehicle outfitted with one or more cameras captures a sequence of images of a rotating propeller. The images are processed according to one or more techniques to recognize a position of the propeller, or an angle of orientation of the propeller, in each of the images. The positions or angles of the rotating propeller are used to calculate a rotational speed of the propeller, or a direction of rotation of the propeller. The cameras used to capture the images are also available for use in other applications such as navigation, monitoring or collision avoidance. The propeller may include one or more stripes, colors, characters, symbols or other markings to enhance its visibility and facilitate the determination of positions or angles of the propeller within images.
-
公开(公告)号：US10563580B2
公开(公告)日：2020-02-18
申请号：US15596239
申请日：2017-05-16
摘要： A sump assembly for use in a gas turbine engine includes a housing and a shaft assembly. The housing is arranged about a central axis of the sump assembly to define a cavity configured to house oil and high-pressure gasses. The shaft assembly is mounted to rotate about the central axis and to direct the high-pressure gasses into the housing.
-
公开(公告)号：US10458258B2
公开(公告)日：2019-10-29
申请号：US14764021
申请日：2013-01-30
摘要： According to an exemplary embodiment of this disclosure, among other possible things a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor section, a plurality of turbine disks in at least one of the compressor section and the turbine sections, at least one cover plate corresponding to at least one of the turbine disks, each of the cover plates includes, at least two snaps connected via a webbing portion, and a bore region radially inward of the at least two snaps and connected to at least one of the at least two snaps via the webbing portion.
-
公开(公告)号：US10374477B2
公开(公告)日：2019-08-06
申请号：US15461654
申请日：2017-03-17
摘要： The present disclosure is directed to an electric machine defining a longitudinal direction, a radial direction, and a circumferential direction, and an axial centerline defined along the longitudinal direction. The electric machine includes a rotor assembly that includes a plurality of carriers arranged along the circumferential direction. Each pair of carriers defines a carrier gap therebetween along the circumferential direction, and each carrier includes a rotor magnet. The rotor assembly further includes an outer ring radially outward of and surrounding the plurality of carriers along the circumferential direction, the outer ring defining a unitary structure.
-
9.发明授权公开(公告)号：US10358923B2
公开(公告)日：2019-07-23
申请号：US15304963
申请日：2015-05-20
发明人： Kazumasa Takata
IPC分类号： F01D1/00 , F01D5/08 , F01D25/12 , F01D9/02 , F02C7/18 , F02C7/32 , F02C9/18 , F02C9/28 , F02C9/52 , F23M5/08 , F23R3/00 , F23R3/26
摘要： A cooling device includes a hot-part cooling system configured to guide air to a hot part of a gas turbine. The hot-part cooling system includes a compressor capable of operating independently of the gas turbine, and is configured to extract air inside a casing of the gas turbine to pressurize the air with the compressor and guide the air to the hot part of the gas turbine. The cooling device further includes a rotor cooling system configured to extract the air inside the casing of the gas turbine and guide the air to a turbine rotor, and a connecting system configured to guide the air pressurized by the compressor to the rotor cooling system while a fuel supply to the gas turbine is stopped.
-
公开(公告)号：US10302007B2
公开(公告)日：2019-05-28
申请号：US15079029
申请日：2016-03-23
发明人： Florian Erdel
摘要： A turbine housing of an exhaust-gas turbocharger may include at least two spiral-shaped exhaust-gas channels separated from one another via a partition. The at least two channels may be delimited radially to the outside by the turbine housing and radially to the inside by at least two spiral tongues. A first spiral tongue may be associated with one of the channels and a second spiral tongue may be associated with the other of the channels. The at least two spiral tongues may extend in opposite directions away from the partition in a direction towards the turbine housing. According to an example, the at least two spiral tongues may be configured such that, under an increasing thermomechanical loading, the first spiral tongue fails before the second spiral tongue.
-
-
-
-
-
-
-
-
-
搜索结果
372 条记录 (耗时 0.022 秒)
