-
公开(公告)号：US11802525B2
公开(公告)日：2023-10-31
申请号：US17647425
申请日：2022-01-07
Applicant: General Electric Company
Inventor： Vinod Chaudhari , Bhaskar Nanda Mondal , Kishanjit Pal , Sushilkumar Shevakari , Ian F. Prentice , Thomas Moniz , Trevor H. Wood , Kishore Ramakrishnan
CPC classification number: F02K5/00 , F04D19/002 , F04D29/36
Abstract: An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.
-
公开(公告)号：US20230220816A1
公开(公告)日：2023-07-13
申请号：US17647425
申请日：2022-01-07
Applicant: General Electric Company
Inventor： Vinod Chaudhari , Bhaskar Nanda Mondal , Kishanjit Pal , Sushilkumar Shevakari , Ian F. Prentice , Thomas Moniz , Trevor H. Wood , Kishore Ramakrishnan
CPC classification number: F02K5/00 , F04D19/002 , F04D29/36
Abstract: An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.
-
公开(公告)号：US11643969B2
公开(公告)日：2023-05-09
申请号：US17232259
申请日：2021-04-16
Applicant: General Electric Company
CPC classification number: F02C7/12 , F04D19/002 , F04D29/58 , F05D2220/323 , F05D2260/20
Abstract: Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.
-
公开(公告)号：US20220341345A1
公开(公告)日：2022-10-27
申请号：US17241242
申请日：2021-04-27
Applicant: General Electric Company
Inventor： Veeraraju Vanapalli , Bhaskar Nanda Mondal , Apostolos Pavlos Karafillis , Kenneth E. Seitzer
Abstract: A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.
-
公开(公告)号：US20220333528A1
公开(公告)日：2022-10-20
申请号：US17232259
申请日：2021-04-16
Applicant: General Electric Company
Abstract: Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.
-
Patent Agency Ranking
公开(公告)号：US11280198B2
公开(公告)日：2022-03-22
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: F01D5/24 , F01D5/08 , F01D1/24 , F02K3/072 , F01D11/00 , F02C7/18 , F01D25/14 , F02C7/12 , F01D1/26
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：US11267577B2
公开(公告)日：2022-03-08
申请号：US16705384
申请日：2019-12-06
Applicant: General Electric Company
Inventor： Bhaskar Nanda Mondal , Arvind Namadevan , Shankar Jayaraman , Keith EJ Blodgett , Arnab Sen
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.
-
公开(公告)号：US10823001B2
公开(公告)日：2020-11-03
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 , F02C3/067 , F02C7/06 , F02C3/107 , F02C3/113 , F02C7/36
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 bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.
-
公开(公告)号：US10677260B2
公开(公告)日：2020-06-09
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
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.
-
公开(公告)号：US10480322B2
公开(公告)日：2019-11-19
申请号：US15870313
申请日：2018-01-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.
-
-
-
-
-
-
-
-
-
Search Results
101
records
(took 0.021 seconds)
