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公开(公告)号：US12092336B2
公开(公告)日：2024-09-17
申请号：US17195131
申请日：2021-03-08
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：US10724741B2
公开(公告)日：2020-07-28
申请号：US15150844
申请日：2016-05-10
Applicant: General Electric Company
Inventor： Shashank Yellapantula , Anthony John Dean , Narendra Digamber Joshi , Mehmet Muhittin Dede , Jin Yan , Owen James Sullivan Rickey
Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.
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公开(公告)号：US10969107B2
公开(公告)日：2021-04-06
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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Patent Agency Ranking
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：US20170328569A1
公开(公告)日：2017-11-16
申请号：US15150844
申请日：2016-05-10
Applicant: General Electric Company
Inventor： Shashank Yellapantula , Anthony John Dean , Narendra Digamber Joshi , Mehmet Muhittin Dede , Jin Yan , Owen James Sullivan Rickey
IPC: F23R3/34
Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.
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公开(公告)号：US20210190320A1
公开(公告)日：2021-06-24
申请号：US17195131
申请日：2021-03-08
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：US09803552B2
公开(公告)日：2017-10-31
申请号：US14927578
申请日：2015-10-30
Applicant: General Electric Company
Inventor： Yuxin Zhang , Obulesu Chatakonda , Soumya Gudiyella , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet , Shashank Yellapantula
CPC classification number: F02C7/222 , F02C7/04 , F23R3/28 , F23R3/286 , F23R2900/00004
Abstract: A fuel injection system for use in a combustor of a turbine assembly includes a substantially annular fuel injection housing at least partially defining an annular cavity. The fuel injection system also includes a fuel manifold and an air manifold. The fuel manifold includes a plurality of fuel injection ports extending through the fuel injection housing. The air manifold includes a first plurality of air injection ports and a second plurality of air injection ports that each extends through the fuel injection housing.
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公开(公告)号：US20170122211A1
公开(公告)日：2017-05-04
申请号：US14927578
申请日：2015-10-30
Applicant: General Electric Company
Inventor： Yuxin Zhang , Obulesu Chatakonda , Soumya Gudiyella , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet , Shashank Yellapantula
CPC classification number: F02C7/222 , F02C7/04 , F23R3/28 , F23R3/286 , F23R2900/00004
Abstract: A fuel injection system for use in a combustor of a turbine assembly includes a substantially annular fuel injection housing at least partially defining an annular cavity. The fuel injection system also includes a fuel manifold and an air manifold. The fuel manifold includes a plurality of fuel injection ports extending through the fuel injection housing. The air manifold includes a first plurality of air injection ports and a second plurality of air injection ports that each extends through the fuel injection housing.
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