公开(公告)号：US20190085722A1

公开(公告)日：2019-03-21

申请号：US15710176

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Peeyush Pankaj ,  Shashank Suresh Puranik ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn ,  Richard Schmidt ,  Bhaskar Nanda Mondal

IPC: F01D25/16 ,  F01D5/30 ,  F02C3/04 ,  F02K3/04

Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.

公开(公告)号：US20190085721A1

公开(公告)日：2019-03-21

申请号：US15710146

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Peeyush Pankaj ,  Shashank Suresh Puranik ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn ,  Richard Schmidt ,  Bhaskar Nanda Mondal ,  Ramana Reddy Kollam

IPC: F01D25/16 ,  F01D5/30 ,  F02C3/04 ,  F02K3/04

Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four total bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.

公开(公告)号：US20190085716A1

公开(公告)日：2019-03-21

申请号：US15710123

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Peeyush Pankaj ,  Shashank Suresh Puranik ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn ,  Richard Schmidt

IPC: F01D15/12 ,  F01D1/26 ,  F01D25/16 ,  F01D5/03

Abstract: A turbomachine includes a turbine section including a turbine center frame and a turbine, the turbine including a plurality of low-speed turbine rotor blades and a plurality of high-speed turbine rotor blades alternatingly spaced along the axial direction. The plurality of low-speed turbine rotor blades each extend between a radially inner end and a radially outer end. At least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the radially outer ends. The turbomachine also includes a gearbox aligned with, or positioned forward of, a midpoint of the turbine. The gearbox includes a first gear coupled to the plurality of low-speed turbine rotor blades, a second gear coupled to the plurality of high-speed turbine rotor blades, and a third gear coupled to the turbine center frame.

公开(公告)号：US20180340470A1

公开(公告)日：2018-11-29

申请号：US15605281

申请日：2017-05-25

Applicant: General Electric Company

Inventor： Alan Roy Stuart ,  Jeffrey Donald Clements ,  Richard Schmidt ,  Thomas Ory Moniz

IPC: F02C7/12 ,  F02C3/06 ,  F02C7/06

Abstract: The present disclosure is directed to a method of turbine section thermal management for a gas turbine engine. The engine includes a first turbine bearing defining an outer air bearing disposed radially adjacent to a low speed turbine rotor hub of a low speed turbine rotor and an inner bearing disposed radially adjacent to a high pressure (HP) shaft coupled to a high speed turbine rotor, wherein a first manifold is in fluid communication from a pressure plenum of a combustion section to the first turbine bearing, and wherein a second manifold is in fluid communication from the first turbine bearing to a pressure regulating valve and an outer diameter secondary flowpath of the turbine section, and wherein a third manifold is in fluid communication from the pressure plenum of the combustion section to the pressure regulating valve. The method includes flowing air from the pressure plenum to the first turbine bearing; flowing air between the outer air bearing and the low speed turbine rotor hub; flowing air between the inner air bearing and the HP shaft; flowing air from the first turbine bearing to the pressure regulating valve via the second manifold; and flowing air from the first turbine bearing to the outer diameter secondary flowpath via the second manifold.

公开(公告)号：US20170030220A1

公开(公告)日：2017-02-02

申请号：US14809560

申请日：2015-07-27

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Richard Schmidt ,  Daniel Alan Niergarth

IPC: F01D25/16 ,  F01D25/20 ,  F02C7/32

CPC classification number: F01D25/164 ,  F01D9/065 ,  F01D25/162 ,  F01D25/18 ,  F01D25/20 ,  F02C7/32 ,  F05D2260/98 ,  Y02T50/671

Abstract: A gas turbine engine is provided including a shaft coupling a compressor of a compressor section to a turbine of a turbine section. An aft bearing assembly, including at least two bearings, is positioned at least partially in an aft sump and supports the shaft within the turbine section. The aft sump is configured to receive lubrication oil from a lubrication oil supply extending through at least a portion of a turbine center frame of the turbine section, and provide such lubrication to the at least two bearings of the aft bearing assembly.

Abstract translation: 提供一种燃气涡轮发动机，其包括将压缩机部分的压缩机联接到涡轮部分的涡轮机的轴。 包括至少两个轴承的后轴承组件至少部分地定位在后水槽中，并将轴支撑在涡轮部分内。 后排池被构造成从润滑油供应部分接收润滑油，所述润滑油供应源延伸穿过涡轮机部分的涡轮机中心框架的至少一部分，并且为后轴承组件的至少两个轴承提供这种润滑。