公开(公告)号：US10508546B2

公开(公告)日：2019-12-17

申请号：US15710109

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: F01D5/03 ,  F01D5/14 ,  F01D1/26 ,  F01D9/04 ,  F02C7/06 ,  F02C7/32 ,  F02C7/36 ,  F02C3/067 ,  F01D25/16

Abstract: A turbomachine includes a turbine section including a turbine, the turbine having a plurality of turbine rotor blades spaced along the axial direction, each turbine rotor blade extending generally along the radial direction between a radial inner end and a radial outer end. The plurality of turbine rotor blades includes a first turbine rotor blade; and a second turbine rotor blade spaced from the first turbine rotor blade along the axial direction, the radial outer end of the first turbine rotor blade coupled to the radial outer end of the second turbine rotor blade. The plurality of turbine rotor blades additionally includes a third turbine rotor blade spaced from the second turbine rotor blade along the axial direction, the radial inner end of the second turbine rotor blade coupled to the radial inner end of the third turbine rotor blade.

公开(公告)号：US10428692B2

公开(公告)日：2019-10-01

申请号：US15303258

申请日：2015-04-13

Applicant: General Electric Company

Inventor： David Walter Parry ,  Christopher Charles Glynn ,  John Creighton Schilling

IPC: F01D25/24 ,  F02C7/20

Abstract: A fairing assembly is provided which is located between a frame hub and an engine casing. The assembly provides for use of a metallic structure in combination with a light weight low alpha material in order to improve engine efficiency and performance. Relative growth between the dissimilar materials is compensated for by a flexible bracket which provides biasing force on one of the assembly components in a cold engine condition as well as allowing for growth at the high temperature operating conditions of the engine.

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：US10227928B2

公开(公告)日：2019-03-12

申请号：US14761698

申请日：2014-01-14

Applicant: General Electric Company

Inventor： Craig Miller Kuhne ,  Christopher Charles Glynn ,  Randy M. Vondrell ,  Andrew Breeze-Stringfellow ,  Kurt David Murrow ,  Darek T. Zatorski ,  Donald Scott Yeager ,  Nicholas Rowe Dinsmore ,  Samuel Jacob Martin ,  Donald Albert Bradley

IPC: F02C7/36 ,  F02C3/073 ,  F02K3/06 ,  F02K3/072 ,  F02C3/107

Abstract: A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the first direction. The first stage blades are directly adjacent to one another, a drive in operable input connection with the fan and in operable output connection with the first stage blades and the second stage blades, the first stage blades and the second stage blades driving the fan through the drive.

公开(公告)号：US09915159B2

公开(公告)日：2018-03-13

申请号：US14574472

申请日：2014-12-18

Applicant: General Electric Company

Inventor： Benjamin Scott Huizenga ,  Christopher Charles Glynn ,  Darrell Glenn Senile ,  Robert Alan Frederick ,  Michael Todd Radwanski ,  Michael Ray Tuertscher ,  Greg Scott Phelps

IPC: F01D9/04 ,  F01D25/16 ,  F02C7/20

CPC classification number: F01D9/047 ,  F01D9/041 ,  F01D25/16 ,  F01D25/162 ,  F02C7/20 ,  F05D2230/642 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.

公开(公告)号：US20180016944A1

公开(公告)日：2018-01-18

申请号：US15210783

申请日：2016-07-14

Applicant: General Electric Company

Inventor： Jared Peter Buhler ,  Christopher Charles Glynn ,  Corey Bourassa ,  Monty Lee Shelton ,  Robert Francis Manning ,  Victor Hugo Silva Correia

IPC: F01D25/32 ,  B01D45/12 ,  B01D46/10 ,  B01D45/04 ,  B01D46/24 ,  B01D46/42 ,  F01D25/12

Abstract: An assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle remover, a second particle remover fluidly coupled which receives a particle-laden stream from the first particle remover, and a venturi having a fluidly coupled to the second particle remover to increase the pressure differential across the assembly.