公开(公告)号：US20200088037A1

公开(公告)日：2020-03-19

申请号：US16675918

申请日：2019-11-06

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Arnab Sen ,  Jeffrey Douglas Rambo ,  Rajesh Kumar ,  Bhaskar Nanda Mondal ,  Alan Roy Stuart ,  Robert Proctor ,  Christopher Charles Glynn

IPC: F01D5/08 ,  F01D25/14 ,  F02C7/12 ,  F01D11/00 ,  F01D1/26 ,  F01D1/24 ,  F02K3/072 ,  F02C7/18

Abstract: An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.

公开(公告)号：US10393149B2

公开(公告)日：2019-08-27

申请号：US15447565

申请日：2017-03-02

Applicant: General Electric Company

Inventor： Bhaskar Nanda Mondal ,  Kenneth Edward Seitzer ,  Monty Lee Shelton ,  Thomas Ory Moniz ,  Atanu Saha

IPC: F04D29/58 ,  F04D29/64 ,  F02K3/06 ,  F04D19/02 ,  F01D11/24

Abstract: The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.

公开(公告)号：US20190257318A1

公开(公告)日：2019-08-22

申请号：US15900891

申请日：2018-02-21

Applicant: General Electric Company

Inventor： Veeraraju Vanapalli ,  Bhaskar Nanda Mondal ,  Jagata Laxmi Narasimharao ,  Tsuguji Nakano ,  Subramanian Narayanan

IPC: F04D29/32 ,  F01D5/06 ,  F01D25/24

Abstract: The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.

公开(公告)号：US20190249599A1

公开(公告)日：2019-08-15

申请号：US15895336

申请日：2018-02-13

Applicant: General Electric Company

Inventor： Arnab Sen ,  Brandon Wayne Miller ,  Bhaskar Nanda Mondal ,  Kishanjit Pal ,  Daniel Alan Niergarth

IPC: F02C6/18 ,  F02C3/04 ,  F02C7/18 ,  F02K3/02

CPC classification number: F02C6/18 ,  F02C3/04 ,  F02C7/18 ,  F02K3/02 ,  F05D2210/20 ,  F05D2220/323 ,  F05D2220/62 ,  F05D2220/76 ,  F05D2260/213

Abstract: An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.

公开(公告)号：US20190093489A1

公开(公告)日：2019-03-28

申请号：US15712234

申请日：2017-09-22

Applicant: General Electric Company

Inventor： Bhaskar Nanda Mondal ,  Ramana Reddy Kollam

IPC: F01D5/30 ,  F01D5/02

Abstract: The present disclosure is directed to an outer drum rotor assembly for a gas turbine engine including a first outer drum and a second outer drum. Each outer drum defines a radially extended flange adjacent to one another. A plurality of outer drum airfoils is extended inward along the radial direction from between the first outer drum and the second outer drum at the flange.

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：US20180363678A1

公开(公告)日：2018-12-20

申请号：US15625212

申请日：2017-06-16

Applicant: General Electric Company

Inventor： Christopher James Kroger ,  Brandon Wayne Miller ,  Trevor Wayne Goerig ,  David William Crall ,  Tsuguji Nakano ,  Jeffrey Donald Clements ,  Bhaskar Nanda Mondal

IPC: F04D29/56 ,  F04D29/54 ,  F04D29/68

CPC classification number: F04D29/563 ,  F01D9/041 ,  F02C3/04 ,  F02C7/04 ,  F02K3/06 ,  F04D29/542 ,  F04D29/545 ,  F04D29/684 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/122 ,  F05D2250/182 ,  F05D2250/184 ,  F05D2260/14

Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades, each of the plurality of fan blades defining a fan blade span along a radial direction. The gas turbine engine further includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide varies attached to the outer nacelle at a location forward of the plurality of fan blades along an axial direction. Each of the plurality of inlet guide vanes defines an IGV span along the radial direction, the IGV span being at least about five percent of the fan blade span and up to about fifty-five percent of the fan blade span.

公开(公告)号：US10087772B2

公开(公告)日：2018-10-02

申请号：US14977098

申请日：2015-12-21

Applicant: General Electric Company

Inventor： Changjie Sun ,  Yu Xie Mukherjee ,  Bhaskar Nanda Mondal ,  Atanu Saha ,  Marcia Boyle Johnson ,  Wenfeng Lu

IPC: F01D11/24 ,  F04D29/58 ,  F04D29/52 ,  F04D29/16

Abstract: The turbomachine includes a rotatable member defining an axis of rotation and an inner annular casing extending circumferentially over at least a portion of the rotatable member. The inner annular casing includes a radially outer surface. The turbomachine further includes an outer annular casing extending over at least a portion of the inner annular casing. The inner annular casing and the outer annular casing define a plurality of cavities therebetween. The clearance control system includes a manifold system including a plurality of conduits extending circumferentially about the inner annular casing and disposed within the cavities. The clearance control system also includes an impingement system extending circumferentially about the inner annular casing and disposed within the cavities. The conduits are configured to channel a flow of cooling fluid to the impingement system which is configured to channel the cooling fluid to the radially outer surface of the inner annular casing.

公开(公告)号：US20180238346A1

公开(公告)日：2018-08-23

申请号：US15438284

申请日：2017-02-21

Applicant: General Electric Company

Inventor： Veeraraju Vanapalli ,  Nitesh Jain ,  Viswanadha Gupta Sakala ,  Bhaskar Nanda Mondal ,  Nicholas Joseph Kray

IPC: F04D29/52 ,  F04D19/00 ,  F04D29/32 ,  F04D29/02

Abstract: A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the plurality of rotor blades and the outer case. The annular ring is configured to restrict thermal contraction of the outer case towards the plurality of rotor blades.