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公开(公告)号：US11572840B2
公开(公告)日：2023-02-07
申请号：US16701574
申请日：2019-12-03
Applicant: General Electric Company
Inventor： Joel Meier Haynes , Sarah Marie Monahan , Thomas Michael Lavertu , Venkat Eswarlu Tangirala , Kapil Kumar Singh
Abstract: A computer-implemented method for multi-mode operation of a combustion system, a combustion system, and a heat engine are provided. The method includes initializing combustion of a fuel/oxidizer mixture, determining whether conditions at the combustion system meet or exceed a first threshold operating parameter, transitioning to detonation combustion of the fuel/oxidizer mixture if conditions at the combustion system meet or exceed the first threshold operating parameter, and maintaining or increasing fuel flow through a deflagrative fuel circuit if conditions at the combustion system do not meet or exceed the first threshold operating parameter.
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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：US10221763B2
公开(公告)日：2019-03-05
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
IPC: F02C5/02 , F02C3/16 , F02C7/264 , F23R7/00 , F02C3/04 , F02K7/08 , F02K7/075 , F02C5/10 , F02C5/00 , F02C3/14 , F23R3/34 , F23R3/42 , F23R3/28 , F23R3/56
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：US20180180289A1
公开(公告)日：2018-06-28
申请号：US15390052
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Thomas Michael Lavertu, Jr. , Andrew Maxwell Peter , Venkat Eswarlu Tangirala , James Albert Tallman , Anthony John Dean
IPC: F23R7/00
CPC classification number: F23R7/00 , F23R3/56 , F23R2900/03041
Abstract: A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture. The rotating detonation combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit extending along at least one of the radially inner side wall or the radially outer side wall. The assembly also includes a first compressor configured to discharge a flow of cooling air towards the rotating detonation combustor, and to channel the flow of cooling air through the cooling conduit.
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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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Patent Agency Ranking
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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公开(公告)号：US20240309830A1
公开(公告)日：2024-09-19
申请号：US18672379
申请日：2024-05-23
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Timothy John Sommerer , Narendra Digamber Joshi , Venkat Eswarlu Tangirala
CPC classification number: F02K7/10 , F02K7/14 , F23R3/12 , F23R2900/00009 , F23R2900/00015
Abstract: An engine includes an inlet tube introducing air to a combustion process and a first plurality of fuel injectors disposed in the inlet tube and used for scram-jet engine operation. The engine includes a second plurality of fuel injectors used for ram-jet engine operation. The second plurality of fuel injectors is upstream from the first plurality of fuel injectors and is disposed in the inlet tube. The engine includes a combustor swirl zone downstream of and adjacent to the first plurality of fuel injectors.
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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：US11149954B2
公开(公告)日：2021-10-19
申请号：US15795894
申请日：2017-10-27
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Narendra Digamber Joshi
Abstract: A rotating detonation combustion system is generally provided. The rotating detonation combustion system includes an outer wall, an upstream wall, and a radial wall. The outer wall is defined circumferentially around a combustor centerline extended along a lengthwise direction. The outer wall defines a first radius portion generally upstream along the outer wall. A second radius portion is defined generally downstream along the outer wall and a transition portion is defined between the first and second radius portions. The first radius portion defines a first radius greater than a second radius at the second radius portion. The transition portion defines a generally decreasing radius from the first radius portion to the second radius portion. The upstream wall is defined circumferentially around the combustor centerline and is extended along the lengthwise direction and inward radially of the first radius portion of the outer wall. An oxidizer passage is defined within the upstream wall. A combustion chamber is defined downstream of the upstream wall and radially inward of the outer wall. The radial wall is coupled to the outer wall and the upstream wall. A fluid injection opening is defined through at least one of the radial wall or the outer wall adjacent to the combustion chamber.
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公开(公告)号：US20210108801A1
公开(公告)日：2021-04-15
申请号：US16601012
申请日：2019-10-14
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Thomas Michael Lavertu , Thomas Earl Dyson , Sarah Marie Monahan , Venkat Eswarlu Tangirala , Joel Meier Haynes
Abstract: Systems for rotating detonation combustion are provided herein. The system includes an inner wall and an outer wall each extended around a centerline axis, wherein a detonation chamber is defined between the inner wall and the outer wall, and an iterative structure positioned at one or both of the inner wall or the outer wall. The iterative structure includes a first threshold structure corresponding to a first pressure wave attenuation and a second threshold structure corresponding to a second pressure wave attenuation. The iterative structure provides for pressure wave strengthening along a first circumferential direction in the detonation chamber or pressure wave weakening along a second circumferential direction opposite of the first circumferential direction. The first circumferential direction corresponds to a desired direction of pressure wave propagation in the detonation chamber.
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