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公开(公告)号：US20200041127A1
公开(公告)日：2020-02-06
申请号：US16051838
申请日：2018-08-01
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Hiranya Kumar Nath , Jayanth Sekar , Arthur Wesley Johnson , Gurunath Gandikota , Mayank Krisna Amble , Clayton Stuart Cooper
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening. The liner includes a walled chute disposed at least partially within the opening. The walled chute defines an inner surface at least partially defining a jet destabilizer.
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公开(公告)号：US20190024895A1
公开(公告)日：2019-01-24
申请号：US15652378
申请日：2017-07-18
Applicant: General Electric Company
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an inner liner and an outer liner together defining a combustion chamber therebetween and a pressure plenum surrounding the inner liner and the outer liner. One or more of the inner liner and the outer liner defines one or more openings. The one or more liners includes a walled chute disposed at least partially within the opening. A structural member extends from the one or more liners to the walled chute.
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公开(公告)号：US11415321B2
公开(公告)日：2022-08-16
申请号：US17029587
申请日：2020-09-23
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A method for regulating jet wakes in a combustor including: directing compressed fluid into a passageway between a casing and a combustor liner; directing a combustion gas along a combustion zone; discharging a first portion of compressed fluid from the passageway into the combustion zone via a first through-hole which is disposed on a section of a combustor panel in a first circumferential row; and discharging a second portion of the compressed fluid from the passageway into the combustion zone via second through-holes, wherein the second through-holes are disposed on a section of the panel, spaced apart axially and circumferentially, and adjacent to the first through-hole, wherein the second through-holes include a first set of through-holes and a second set of through-holes, the first set of through-holes in a second row and the second set of through-holes in a third row, wherein the second and third rows extend circumferentially.
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公开(公告)号：US11255543B2
公开(公告)日：2022-02-22
申请号：US16057249
申请日：2018-08-07
Applicant: General Electric Company
Inventor： Mayank Krisna Amble , Gurunath Gandikota , Perumallu Vukanti , Ravi Chandra , Karthikeyan Sampath
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening and includes a walled chute disposed at least partially through the opening. A plurality of flow openings is defined through the walled chute.
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公开(公告)号：US20190249874A1
公开(公告)日：2019-08-15
申请号：US15896223
申请日：2018-02-14
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Hiranya Kumar Nath , Arvind Kumar Rao , Steven Clayton Vise , Perumallu Vukanti , Mayank Krisna Amble , Clayton Stuart Cooper
CPC classification number: F23R3/002 , F23R3/08 , F23R3/14 , F23R3/16 , F23R2900/03042
Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.
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Patent Agency Ranking
公开(公告)号：US20210278085A1
公开(公告)日：2021-09-09
申请号：US16808443
申请日：2020-03-04
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Steven Clayton Vise , Perumallu Vukanti , Mayank Krisna Amble , Clayton Stuart Cooper , Nicholas Ryan Overman , Karthikeyan Sampath , Allen Michael Danis , Craig Douglas Young
Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.
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公开(公告)号：US20210003281A1
公开(公告)日：2021-01-07
申请号：US17029587
申请日：2020-09-23
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A method for regulating jet wakes in a combustor including: directing compressed fluid into a passageway between a casing and a combustor liner; directing a combustion gas along a combustion zone; discharging a first portion of compressed fluid from the passageway into the combustion zone via a first through-hole which is disposed on a section of a combustor panel in a first circumferential row; and discharging a second portion of the compressed fluid from the passageway into the combustion zone via second through-holes, wherein the second through-holes are disposed on a section of the panel, spaced apart axially and circumferentially, and adjacent to the first through-hole, wherein the second through-holes include a first set of through-holes and a second set of through-holes, the first set of through-holes in a second row and the second set of through-holes in a third row, wherein the second and third rows extend circumferentially.
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公开(公告)号：US20200049349A1
公开(公告)日：2020-02-13
申请号：US16057249
申请日：2018-08-07
Applicant: General Electric Company
Inventor： Mayank Krisna Amble , Gurunath Gandikota , Perumallu Vukanti , Ravi Chandra , Karthikeyan Sampath
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening and includes a walled chute disposed at least partially through the opening. A plurality of flow openings is defined through the walled chute.
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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：US11280495B2
公开(公告)日：2022-03-22
申请号：US16808443
申请日：2020-03-04
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Steven Clayton Vise , Perumallu Vukanti , Mayank Krisna Amble , Clayton Stuart Cooper , Nicholas Ryan Overman , Karthikeyan Sampath , Allen Michael Danis , Craig Douglas Young
Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.
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