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公开(公告)号：US20190086091A1
公开(公告)日：2019-03-21
申请号：US15705954
申请日：2017-09-15
Applicant: General Electric Company
Inventor： Owen James Sullivan Rickey , Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Shashank Yellapantula
Abstract: A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.
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公开(公告)号：US20190017437A1
公开(公告)日：2019-01-17
申请号：US15649093
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Aaron Glaser , Sibtosh Pal , Narendra Digamber Joshi
Abstract: A gas turbine engine includes a primary combustor, a secondary combustor, a high pressure (HP) turbine, and a mixing duct. The HP turbine is downstream of the primary combustor and fluidly connected to a rear end of the primary combustor via a first exhaust duct. The mixing duct is disposed downstream of the HP turbine and the secondary combustor. The mixing duct has a first inlet fluidly connected to the HP turbine via a turbine exit duct, a second inlet fluidly connected to a rear end of the secondary combustor via a second exhaust duct, and an outlet. The turbine exit duct directs a primary exhaust stream, which is emitted from the primary combustor and expanded through the HP turbine, into the mixing duct. The second exhaust duct directs a secondary exhaust stream emitted from the secondary combustor into the mixing duct.
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Patent Agency Ranking
公开(公告)号：US10072846B2
公开(公告)日：2018-09-11
申请号：US14791684
申请日：2015-07-06
Applicant: General Electric Company
Inventor： Sarah Marie Monahan , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet
IPC: F23R3/28 , F23R3/34 , F23C5/08 , F23R3/58 , F23R3/12 , F23R3/04 , F23C5/00 , F23R3/42 , F23C5/32 , F23R3/02 , F23R3/10 , F23C5/24 , F23R3/06
CPC classification number: F23R3/286 , F05D2240/35 , F23C5/00 , F23C5/08 , F23C5/10 , F23C5/24 , F23C5/32 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/10 , F23R3/12 , F23R3/34 , F23R3/346 , F23R3/42 , F23R3/58 , F23R2900/00015 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
Abstract: A gas turbine engine and combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two axially spaced apart annular trapped vortex cavities are located on the combustor liner and staged axially and radially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities. A plurality of injectors are configured tangentially relative to circular radially outer wall extending between an aft wall and a forward wall of each cavity to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid.
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公开(公告)号：US20180179953A1
公开(公告)日：2018-06-28
申请号：US15390105
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Andrew Maxwell Peter , Kapil Kumar Singh , Keith Robert McManus , Joel Haynes , Anthony Dean
CPC classification number: F02C5/02 , F02C3/04 , F02C3/14 , F02C3/16 , F02C3/165 , F02C5/00 , F02C5/10 , F02C7/264 , F02K7/075 , F02K7/08 , F05D2220/32 , F05D2240/35 , F23R3/286 , F23R3/34 , F23R3/42 , F23R3/56 , F23R7/00
Abstract: A combustor is configured to operate in a rotating detonation mode and a deflagration mode. The combustor includes a housing and at least one initiator. The housing defines at least one combustion chamber and is configured for a deflagration process to occur within the at least one combustion chamber during operation in the deflagration mode and a rotating detonation process to occur within the at least one combustion chamber during operation in the rotating detonation mode. The at least one initiator is configured to initiate the rotating detonation process within the at least one combustion chamber during operation in the rotating detonation mode and to initiate the deflagration process within the at least one combustion chamber during operation in the deflagration mode.
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公开(公告)号：US20180179952A1
公开(公告)日：2018-06-28
申请号：US15390120
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Andrew Maxwell Peter , Peter Daniel Silkowski , Thomas Michael Lavertu , Venkat Eswarlu Tangirala , Douglas Carl Hofer
CPC classification number: F02C3/16 , F01D5/02 , F02C3/04 , F02C5/02 , F02C9/28 , F05D2220/32 , F05D2240/35 , Y02E20/16
Abstract: A turbine engine includes a rotating detonation combustor including a housing defining at least one combustion chamber. The rotating detonation combustor is configured for a rotating detonation process to occur within the at least one combustion chamber to generate a combustion flow including a first portion and a second portion. The turbine engine also includes a turbine coupled in flow communication with the rotating detonation combustor. The turbine is configured to receive the combustion flow from the rotating detonation combustor. The turbine includes a first blade and a second blade that rotate about an axis at a rotational frequency. The rotating detonation combustor and the turbine are configured for the combustion flow first portion to contact the first blade substantially continuously as the first blade rotates.
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公开(公告)号：US20180179950A1
公开(公告)日：2018-06-28
申请号：US15390024
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Andrew Maxwell Peter , Peter Daniel Silkowski , Thomas Michael Lavertu , Venkat Eswarlu Tangirala , Douglas Carl Hofer
CPC classification number: F02C3/16 , F02C5/02 , F05D2240/35 , F23R7/00
Abstract: A turbine engine assembly including a plurality of rotating detonation combustors configured for a rotating detonation process to occur to produce a flow of combustion gas. The plurality of rotating detonation combustors are oriented such that the flow of combustion gas discharged therefrom flows helically relative to a centerline of the turbine engine assembly. The assembly also includes a turbine coupled downstream from the plurality of rotating detonation combustors. The turbine is configured to receive the flow of combustion gas.
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公开(公告)号：US20170089205A1
公开(公告)日：2017-03-30
申请号：US14870853
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Christian Lee Vandervort , Krishan Lal Luthra , Ronald Scott Bunker , Joel Meier Haynes , Venkat Eswarlu Tangirala
CPC classification number: F01D5/186 , F01D25/32 , F02C3/34 , F02C6/003 , F02C7/185 , F05D2260/213 , F05D2260/61 , F05D2300/6033 , F23C9/08 , F23M2900/05004 , F23N2021/12 , F23R3/002 , F23R2900/03041 , F23R2900/03341 , Y02E20/14 , Y02E20/16
Abstract: A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.
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