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公开(公告)号：US20240271528A1
公开(公告)日：2024-08-15
申请号：US18308105
申请日：2023-04-27
Applicant: General Electric Company
Inventor： Vaishnav Raghuvaran , Bhaskar Nanda Mondal , Gary Willard Bryant, JR.
CPC classification number: F01D5/021 , F01D5/3007 , F01D11/008 , F05D2220/36 , F05D2230/60
Abstract: A fan assembly includes a disk having a disk forward surface, a disk aft surface, and a radially outer surface. The disk defines a plurality of disk posts and a plurality of disk slots in the radially outer surface. At least one of the plurality of disk posts includes a post slot. The fan assembly also includes a fan having a plurality of fan blades and a plurality of platforms extending between adjacent fan blades of the plurality of fan blades. Each of the plurality of fan blades is received within one of the plurality of disk slots via a respective blade root. Further, the fan assembly includes at least one fan retention member having a body portion and a protrusion extending from the body portion. The protrusion is received within the post slot such that the at least one fan retention member supports one of the plurality of platforms.
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公开(公告)号：US11724813B2
公开(公告)日：2023-08-15
申请号：US18058040
申请日：2022-11-22
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Bhaskar Nanda Mondal , Arda Unsal
CPC classification number: B64D27/10 , F02C3/04 , F02C7/06 , F02C7/36 , F05D2240/60 , F05D2260/40 , F05D2260/96 , F05D2300/211 , F05D2300/2112 , F05D2300/2261 , F05D2300/6033 , F05D2300/614
Abstract: A turbomachine engine including a high-pressure compressor, a high-pressure turbine, a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, and a power turbine in flow communication with the high-pressure turbine. At least one of the high-pressure compressor, the high-pressure turbine, and the power turbine comprises a ceramic matrix composite (CMC) material. The turbomachine engine includes a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft.
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公开(公告)号：US20220268209A1
公开(公告)日：2022-08-25
申请号：US17181773
申请日：2021-02-22
Applicant: General Electric Company
Inventor： Vinod Shashikant Chaudhari , Bhaskar Nanda Mondal , Tsuguji Nakano , David W. Crall
Abstract: Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.
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公开(公告)号：US20220205387A1
公开(公告)日：2022-06-30
申请号：US17139138
申请日：2020-12-31
Applicant: General Electric Company
Abstract: A gas turbine engine having an interdigitated turbine assembly including a first turbine rotor and a second turbine rotor, wherein a total number of stages at the interdigitated turbine assembly is between 3 and 8, and an average stage pressure ratio at the interdigitated turbine assembly is between 1.3 and 1.9. A gear assembly is configured to receive power from the interdigitated turbine assembly, and a fan assembly is configured to receive power from the gear assembly. The interdigitated turbine assembly and the gear assembly are together configured to allow the second turbine rotor to rotate at a second rotational speed greater than a first rotational speed at the first turbine rotor. The fan assembly and the gear assembly are together configured to allow the fan assembly to rotate at a third rotational speed less than the first rotational speed and the second rotational speed. The interdigitated turbine assembly, the gear assembly, and the fan assembly together have a maximum AN2 at the second turbine rotor between 30 and 90.
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公开(公告)号：US11365629B1
公开(公告)日：2022-06-21
申请号：US17230826
申请日：2021-04-14
Applicant: General Electric Company
Inventor： Bhaskar Nanda Mondal , Vinod Shashikant Chaudhari , Rajesh Kumar , Thomas Ory Moniz
Abstract: A turbine assembly including a first rotor assembly with a rotatable outer drum from which one or more stages of a plurality of outer drum airfoils is extended radially inward is provided. An outer casing surrounds the outer drum of the first rotor assembly. A seal assembly is coupled to the outer casing and positioned radially outward from an upstream-most stage of the plurality of outer drum airfoils. The seal assembly is positioned in axial alignment with the upstream-most stage of the plurality of outer drum airfoils. The seal assembly separates a first plenum from a second plenum. The second plenum is formed axially aft of the first plenum and is formed by the seal assembly, the outer casing, and the outer drum of the first rotor assembly. The first plenum is positioned radially outward from the upstream-most stage of the plurality of outer drum airfoils.
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Patent Agency Ranking
公开(公告)号：US11085309B2
公开(公告)日：2021-08-10
申请号：US15712234
申请日：2017-09-22
Applicant: General Electric Company
Inventor： Bhaskar Nanda Mondal , Ramana Reddy Kollam
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.
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公开(公告)号：US20210156279A1
公开(公告)日：2021-05-27
申请号：US16697350
申请日：2019-11-27
Applicant: General Electric Company
Inventor： Shashank Suresh Puranik , Bhaskar Nanda Mondal , Richard Schmidt , Peeyush Pankaj , Narayanan Payyoor
IPC: F01D25/16 , F04D29/059
Abstract: A rotor support system for a gas turbine engine includes a rotatable drum rotor and a non-rotatable support casing. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the non-rotatable support casing. The bearing assembly includes, at least, a stationary support frame and a rotatable race. Further, the rotatable race is configured to engage the rotatable drum rotor at separate and discrete locations that are circumferentially spaced apart around the rotatable drum rotor.
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公开(公告)号：US10823191B2
公开(公告)日：2020-11-03
申请号：US15922153
申请日：2018-03-15
Applicant: General Electric Company
Inventor： Veeraraju Vanapalli , Bhaskar Nanda Mondal , Rajendra Mahadeorao Wankhade , Ramana Reddy Kollam
Abstract: The present disclosure is directed to a gas turbine engine including a first frame comprising a first bearing assembly, a second frame comprising a second bearing assembly, and a compressor rotor. A first stage compressor airfoil is defined at an upstream-most stage of the compressor rotor. The compressor rotor is rotatable via the first bearing assembly and the second bearing assembly. The first stage compressor airfoil is disposed between the first bearing assembly and the second bearing assembly.
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公开(公告)号：US10323571B2
公开(公告)日：2019-06-18
申请号：US14971354
申请日：2015-12-16
Applicant: General Electric Company
Inventor： Sesha Subramanian , Bhaskar Nanda Mondal , Sushilkumar Gulabrao Shevakari , Mayank Krisna Amble
Abstract: A method of heating a hollow structure and a heating system are provided. The system includes a plurality of hollow structures spaced circumferentially about an annular flow path. The hollow structures include a heating fluid inlet port, a first plurality of film heating apertures, and a second plurality of film heating apertures. The hollow structures also include a first internal passage extending between the heating fluid inlet port and the first plurality of film heating apertures. The first internal passage includes an impingement leg configured to channel a first flow of heating fluid to a leading edge of the hollow structure. A second internal passage extends between the heating fluid inlet port and the second plurality of film heating apertures through a path along an inner surface of the hollow structure before being channeled to the second plurality of film heating apertures.
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公开(公告)号：US20190085702A1
公开(公告)日：2019-03-21
申请号：US15710164
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
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 an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.
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