-
公开(公告)号：US20220372915A1
公开(公告)日：2022-11-24
申请号：US17323088
申请日：2021-05-18
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Steven Clayton Vise , Clayton S. Cooper , Michael A. Benjamin
IPC: F02C7/22
Abstract: A gas turbine engine that is configured to mitigate fuel coupled dynamics. The engine includes a combustor, a fuel delivery system, a fuel manifold line; and a device configured to mitigate fuel coupled dynamics. The device is attached to the fuel manifold line and includes a housing and a reflector. The housing includes a wall and the wall defines a housing surface that is configured to reflect waves conducted by fuel within the fuel delivery system. The reflector is positioned within the housing and the reflector includes an anterior surface that is configured to reflect waves conducted by fuel within the fuel delivery system such that wave the reflected waves can strike the surface.
-
公开(公告)号：US20220372913A1
公开(公告)日：2022-11-24
申请号：US17324451
申请日：2021-05-19
Applicant: General Electric Company
Inventor： Hiranya Nath , Michael A. Benjamin , Rajendra Wankhade , Hari Chandra
Abstract: A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.
-
公开(公告)号：US20220349581A1
公开(公告)日：2022-11-03
申请号：US17860990
申请日：2022-07-08
Applicant: General Electric Company
Inventor： Brett A. Rich , Michael A. Benjamin , Nicholas R. Overman , Aaron J. Glaser
Abstract: In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture configured to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first channel directing a first air stream into the fuel conduit; and a second channel directing a second air stream into the fuel conduit. The first air stream and the second air stream cooperatively shape the fuel jet coming out of the fuel window.
-
公开(公告)号：US11421885B2
公开(公告)日：2022-08-23
申请号：US17231771
申请日：2021-04-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen , Michael A. Benjamin
Abstract: A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.
-
公开(公告)号：US11408610B1
公开(公告)日：2022-08-09
申请号：US17166477
申请日：2021-02-03
Applicant: General Electric Company
Inventor： Brett A. Rich , Michael A. Benjamin , Nicholas R. Overman , Aaron J. Glaser
Abstract: In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to cooperatively shape the fuel jet coming out of the fuel window.
-
Patent Agency Ranking
公开(公告)号：US20220178540A1
公开(公告)日：2022-06-09
申请号：US17115877
申请日：2020-12-09
Applicant: General Electric Company
Inventor： Hari Ravi Chandra , Arvind Kumar Rao , Shai Birmaher , Jayanth Sekar , Gurunath Gandikota , Michael A. Benjamin
Abstract: A mixing assembly for a combustor, including: a pilot mixer and a pilot fuel nozzle; a main mixer including: a main housing surrounding the pilot mixer; a fuel manifold positioned between the pilot housing and the main housing; a mixer foot extending outward from a forward end of the main housing; a main swirler body surrounding the main housing such that an annular mixing channel is defined between the main housing and the main swirler body, and coupled to the mixer foot; and a main fuel ring in the mixing channel downstream of the mixer foot connected to the main housing by main fuel vanes, at least one of the main fuel ring and the main fuel vanes including fuel injection ports positioned to discharge fuel into a central portion of the mixing channel, wherein the mixer foot extends farther from the main housing than the main fuel ring.
-
公开(公告)号：US20250129748A1
公开(公告)日：2025-04-24
申请号：US18492002
申请日：2023-10-23
Applicant: General Electric Company
Inventor： Pradeep Naik , Clayton S. Cooper , Steven C. Vise , Michael A. Benjamin , Steven Marakovits , Sibtosh Pal , Sripathi Mohan
Abstract: A turbine engine has a combustor in a core air flow path that generates combustion gases and a fuel and steam system fluidly coupled to the combustor. The fuel and steam system has a steam system to provide a steam flow to the combustor and a fuel system to provide a primary fuel flow and a secondary fuel flow to the combustor. The fuel system has a first state in which there is a first flow rate of the secondary fuel flow to the combustor and a second state in which there is a second flow rate of the secondary fuel flow to the combustor. The first flow rate and the second flow rate are different. The first state and the second state are based on a condition of the steam system.
-
公开(公告)号：US12255363B2
公开(公告)日：2025-03-18
申请号：US17396401
申请日：2021-08-06
Applicant: General Electric Company
Inventor： Honggang Wang , Michael A. Benjamin , Seung-Hyuck Hong , Richard L. Hart
IPC: H01M8/04111 , H01M8/04746 , H01M8/2457
Abstract: An integrated fuel cell and combustor assembly includes a combustor that is fluidly coupled with at least one upstream compressor that generates compressed air. A fuel cell stack having a cathode and an anode is fluidly coupled to the combustor. The fuel cell stack is configured to receive intake fuel and a portion of the compressed air as intake air, to generate a fuel cell power output using the intake fuel and the intake air, and to direct a fuel and air exhaust from the fuel cell stack into the combustor. A self-reliant air supply system is fluidly coupled with the at least one upstream compressor and the fuel cell stack, and is configured to supply the intake air to the fuel cell stack. A fault-tolerant controller is configured to detect a transient event within the combustor and to control the self-reliant air supply system during the transient event.
-
公开(公告)号：US12228286B1
公开(公告)日：2025-02-18
申请号：US18477597
申请日：2023-09-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Hiranya Kumar Nath , Perumallu Vukanti , Clayton S. Cooper , Steven C. Vise , Michael A. Benjamin , R Narasimha Chiranthan
Abstract: A combustion section of a turbine engine having a primary combustion chamber and a secondary combustion chamber. The primary combustion chamber is defined, at least in part, by a combustor liner and a dome wall. A primary fuel nozzle having an outlet is located at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber. At least one opening located in an outer liner axially aft of the dome wall fluidly couples the secondary combustion chamber and the primary combustion chamber. A set of secondary fuel nozzles are fluidly coupled with the secondary combustion chamber.
-
公开(公告)号：US12221926B2
公开(公告)日：2025-02-11
申请号：US17805986
申请日：2022-06-08
Applicant: General Electric Company
Inventor： Hejie Li , Shai Birmaher , Michael A. Benjamin
Abstract: A gas turbine engine including a combustor, a plurality of fuel nozzles, and at least one fuel manifold. The combustor includes a combustion chamber. The plurality of fuel injects fuel into the combustion chamber of the combustor. The gas turbine engine may include a first fuel circuit and a second fuel circuit. The first fuel circuit includes a first fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a first temperature. The second fuel circuit includes a second fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a second. The second temperature is less than the first temperature.
-
-
-
-
-
-
-
-
-
Search Results
141
records
(took 0.022 seconds)
