公开(公告)号：US20200157964A1

公开(公告)日：2020-05-21

申请号：US16194653

申请日：2018-11-19

Applicant: General Electric Company

Inventor： Rodrigo Rodriguez Erdmenger ,  Nathan Evan McCurdy Gibson ,  Quang Tue Nguyen Tran ,  Antonio Guijarro Valencia

IPC: F01D11/16

Abstract: An aspect of the present disclosure is directed to a seal assembly. The seal assembly includes a fluid bearing wall including a bearing face defining a fluid opening through the fluid bearing wall. The seal assembly further includes a tilt member is extended from and attached to the fluid bearing wall. The tilt member defines a fluid passage therethrough in fluid communication with the fluid opening at the bearing face of the fluid bearing wall. The seal assembly still further includes a seal body surrounding the tilt member. A cavity is defined between the tilt member and the seal body. The seal assembly further includes a spring member coupled to the seal body and the fluid bearing wall. A passage is defined between the fluid bearing wall and the seal body.

公开(公告)号：US20200157961A1

公开(公告)日：2020-05-21

申请号：US16194673

申请日：2018-11-19

Applicant: General Electric Company

Inventor： Rodrigo Rodriguez Erdmenger ,  Nathan Evan McCurdy Gibson ,  Quang Tue Nguyen Tran ,  Antonio Guijarro Valencia

IPC: F01D11/02 ,  F01D11/06 ,  F01D11/00

Abstract: An aspect of the present disclosure is directed to a seal assembly for a turbo machine. The seal assembly includes a fluid bearing wall including a bearing face in which the bearing face defines a fluid opening through the fluid bearing wall. The seal assembly further includes a seal body extended circumferentially relative to a centerline axis. The seal body defines a cavity extended at least partially circumferentially through the seal body. A fluid passage is defined through the seal body in fluid communication with the fluid opening through the fluid bearing wall.

公开(公告)号：US10145263B2

公开(公告)日：2018-12-04

申请号：US15155823

申请日：2016-05-16

Applicant: General Electric Company

Inventor： Rodrigo Rodriguez Erdmenger ,  Sebastian Walter Freund ,  Ismail Hakki Sezal ,  Aneesh Sridhar Vadvadgi

IPC: F01D17/14 ,  F01D9/04 ,  F01D25/24 ,  F02B33/40 ,  F02B39/16

Abstract: A nozzle assembly of a turbocharger includes a nozzle and a ring-shaped body. The nozzle has flow passages extending through the nozzle and configured to direct air received from a volute housing of the turbocharger through the nozzle to turbine blades of the turbocharger. The ring-shaped body is coupled with the nozzle and is configured to rotate around the nozzle. The ring-shaped body includes blocking segments that block the flow of the air and openings between the blocking segments that permit the air to flow through the ring-shaped body. The ring-shaped body is configured to rotate relative to the nozzle to change how many of the flow passages in the nozzle are blocked by the blocking segments of the ring-shaped body.

公开(公告)号：US09976420B2

公开(公告)日：2018-05-22

申请号：US14807376

申请日：2015-07-23

Applicant: General Electric Company

Inventor： Quang Tue Nguyen Tran ,  Rodrigo Rodriguez Erdmenger ,  Christopher Jon Potokar

IPC: F01D5/04 ,  F01D11/02

CPC classification number: F01D5/046 ,  F01D5/048 ,  F01D11/025 ,  Y02E20/14 ,  Y02T50/673

Abstract: An aspirating seal assembly for use in a turbine engine is provided. The aspirating seal assembly includes a face seal and a rotary component. The face seal includes a first annular seal surface, and the rotary component includes a second annular seal surface positioned adjacent the first annular seal surface and defining a seal interface therebetween. The face seal is configured to discharge a flow of air towards the seal interface. The seal assembly also includes a first seal member extending between the first and second annular seal surfaces such that the flow of air induces a back pressure across the seal interface, and a second seal member positioned radially inward from the first seal member and extending between the first and second annular seal surfaces. A length of the second seal member is selected to increase the back pressure induced across the seal interface.

公开(公告)号：US09500122B2

公开(公告)日：2016-11-22

申请号：US13931191

申请日：2013-06-28

Applicant: General Electric Company

Inventor： Cathal Clancy ,  Daniel Edward Loringer ,  Rodrigo Rodriguez Erdmenger ,  Vittorio Michelassi

IPC: F02B37/24 ,  F02B37/013 ,  F02B37/00 ,  F01D17/16 ,  F01D5/14

CPC classification number: F02B37/24 ,  F01D5/146 ,  F01D17/162 ,  F01D17/167 ,  F02B37/004 ,  F02B37/013 ,  F05D2220/40 ,  Y02T10/144

Abstract: The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.

Abstract translation: 该方法包括移动第一支撑件和第二支撑件中的至少一个以改变多个主叶片和串联叶片相对于彼此的位置，以控制跨越涡轮机的一个或多个流量控制特性。 涡轮机包括具有多个主叶片和串联叶片的喷嘴。 多个主叶片联接到第一支撑件并且多个串联叶片联接到与第一支撑件间隔开设置的第二支撑件。