-
公开(公告)号：US12228079B1
公开(公告)日：2025-02-18
申请号：US18499175
申请日：2023-10-31
Applicant: Texas Fueling Services, Inc.
Inventor： Paul Briggs
Abstract: Embodiments of the present disclose relate to a system of distributing fuel gas. The system of distributing fuel gas includes a vaporizer and compression system (VCS). The VCS includes a vaporizer, a compressor configured to produce compressed fuel gas (CFG) from LFG, and a mounting base. The vaporizer includes a fuel gas inlet configured to provide LFG to the vaporizer from a LFG source, and a fuel gas outlet. The compressor includes a distribution outlet, an exhaust, and a fan. The fan is configured to flow air and gas emitted from the exhaust toward the vaporizer. The vaporizer and the compressor are disposed on the mounting base.
-
公开(公告)号：US20240301835A1
公开(公告)日：2024-09-12
申请号：US18254865
申请日：2021-11-26
Applicant: Siemens Energy Global GmbH & Co. KG
Inventor： Brian Beesley , Ghenadie Bulat
CPC classification number: F02C9/28 , F02C7/228 , F05D2240/35 , F05D2270/095 , F05D2270/31
Abstract: A method of controlling a combustor of a gas turbine engine, the method comprising the steps
supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fuel quantity and a main fuel quantity via a scheduled pilot fuel split, the pilot fuel split is the percentage of the pilot fuel quantity of the total fuel quantity,
monitoring combustion instability,
applying a steady state active pilot split offset to the scheduled pilot fuel split when a predetermined temperature of the combustor is exceeded and/or a predetermined value of combustion instability is exceeded to create a steady state pilot fuel split,
monitoring a condition of the gas turbine engine that influences an air/fuel ratio in the combustor,
disabling the steady state active pilot split offset when the condition of the gas turbine engine is indicative of a transient condition and when a threshold value of combustion instability is exceeded, and
applying a transient active pilot split offset to the steady state pilot fuel split while maintaining the total fuel quantity being supplied at any point in time, the transient active pilot split offset and the steady state active pilot split offset result in a total split offset,
the total split offset being greater than the steady state active pilot split offset and the rate of change of the transient active pilot split offset is faster than the rate of change of the steady state active pilot split offset.-
公开(公告)号：US11970977B2
公开(公告)日：2024-04-30
申请号：US17896786
申请日：2022-08-26
Applicant: Hamilton Sundstrand Corporation
Inventor： Murtuza Lokhandwalla , Brandon P. Williams , Jason A. Ryon , Todd Haugsjaahabink
Abstract: A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal. The auxiliary fuel circuit joins with the secondary fuel circuit for delivery to a fuel nozzle.
-
公开(公告)号：US11965654B2
公开(公告)日：2024-04-23
申请号：US17376494
申请日：2021-07-15
Applicant: Delavan Inc.
Inventor： Lev A. Prociw , Timothy Griffith
CPC classification number: F23R3/283 , F02C7/222 , F02C7/228 , F23R3/346 , F02C7/224 , F05D2260/232 , F23D14/78 , F23D2214/00 , F23R3/28
Abstract: A fuel system includes a fuel supply system. A plurality of fuel nozzles are connected in fluid communication with the fuel supply system to supply fuel from a fuel source to be issued for combustion from the fuel nozzles. A cooling system is included, wherein at least one of the fuel nozzles includes a cooling circuit in addition to a fuel circuit for issuing fuel from the fuel supply system for combustion. The cooling circuit includes an inlet and an outlet. The inlet is in fluid communication with the cooling system for circulation of coolant through the cooling circuit and back to the cooling system out the outlet of the cooling circuit for cooling the fuel circuit with the fuel circuit staged off.
-
公开(公告)号：US11959420B2
公开(公告)日：2024-04-16
申请号：US16736970
申请日：2020-01-08
Applicant: RTX Corporation
Inventor： Timothy S. Snyder
CPC classification number: F02C7/228 , F02C7/232 , F02C9/263 , F05D2220/323 , F05D2270/303 , F23D2900/00015 , F23K2300/206 , F23N2235/24
Abstract: A fuel delivery system for a combustor of a gas turbine engine including a primary fuel tank configured to store a primary fuel, a secondary fuel tank configured to store a secondary fuel, a swirler configured to produce a main flame within a combustion chamber of the combustor, and a fuel nozzle configured to produce a pilot flame within the combustion chamber of the combustor. The fuel nozzle includes a nozzle outlet that is located proximate to an end of the swirler or at the end of the swirler, the end of the swirler being located at an inlet of the combustor. The fuel delivery system also includes a primary fuel line fluidly connecting the primary fuel tank to the fuel nozzle and a secondary fuel line fluidly connecting the secondary fuel tank to the swirler.
-
Patent Agency Ranking
公开(公告)号：US11639700B2
公开(公告)日：2023-05-02
申请号：US17014884
申请日：2020-09-08
Applicant: Hypersonix IP Holdings, Inc.
Inventor： Michael Kevin Smart
Abstract: Airframe integrated scramjet engines are disclosed. Scramjet engines within the scope of this disclosure may be configured to integrate smoothly with an airframe of a hypersonic flight aircraft or vehicle. The scramjet engine may include capture shape of an inlet configured to capture airflow, a combustor configured for combustion of fuel and air, and an exit shape of a nozzle configured for expansion of the combusted fuel and air to provide hypersonic thrust. In some embodiments, the scramjet engine has a fixed geometry and a transitioning cross-sectional shape over its full length. The scramjet engine is configured to be a component of launch vehicle system.
-
公开(公告)号：US20230046593A1
公开(公告)日：2023-02-16
申请号：US17792049
申请日：2020-10-16
Applicant: Siemens Energy Global GmbH & Co. KG
Inventor： Eberhard Deuker , Benedict Kriegler
Abstract: A method for controlling a combustion process in a gas turbine wherein a combustion chamber, a control device storing a calculation model of the combustion process, and an exhaust air measurement device are used. A permissible limit value for nitrogen oxides and for carbon monoxide as pollutants is set. The actual value of at least one of the two pollutants is measured continuously in the exhaust air. When a signal to reduce the power of the gas turbine to a lowest possible value is given, then a minimum fuel supply at which the limit values are complied with is calculated. The fuel supply is then reduced either until the calculated minimum fuel supply is reached or until the continuously measured proportion of the pollutant reaches the permissible limit value.
-
公开(公告)号：US11506389B2
公开(公告)日：2022-11-22
申请号：US17660105
申请日：2022-04-21
Applicant: General Electric Company
Inventor： Jason Nathaniel Cook , Jason Dean Fuller , Christopher James Wenner
Abstract: A loading/unloading method for a gas turbine system is disclosed. The gas turbine system includes a combustion section featuring a primary combustion stage with a first plurality of fuel nozzles and a downstream, secondary combustion stage with a second plurality of fuel nozzles. For loading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a higher number of at least one of the first or second plurality of fuel nozzles; and for unloading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a lower number of at least one of the first or second plurality of fuel nozzles. During each combustion mode, regardless of whether loading or unloading, a primary combustion stage exit temperature of a combustion gas flow is controlled to be within a predefined target range corresponding to the respective combustion mode.
-
公开(公告)号：US11499481B2
公开(公告)日：2022-11-15
申请号：US15323125
申请日：2015-07-01
Applicant: Nuovo Pignone Tecnologie S.R.L.
Inventor： Simone Chechi
Abstract: A fuel distribution device is provided wherein an axis is defined. The device comprises a body housing a distribution path for fuel; the distribution path has one inlet and a plurality of outlets; the inlet is located on the external surface of the body at an end of an inlet branch of the distribution path; the plurality of outlets are located on the external surface of the body at ends of a corresponding plurality of outlet branches of the distribution path; the inlet branch and the outlet branches are fluidly connected to a distribution space; and the outlet branches are arranged radially.
-
公开(公告)号：US11466625B2
公开(公告)日：2022-10-11
申请号：US16957648
申请日：2018-12-21
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: A method for controlling the fuel injection of a turbine engine using a fuel supply circuit. The supply circuit includes a pilot injection line and a main injection line. During a transition of the supply distribution between the pilot injection line and the main supply line, the method includes the following steps: a) determining at least a minimum value to be maintained for a pressure value; b) determining at least one hydraulic quantity of the supply circuit; c) based on the determined hydraulic quantity of the supply circuit, calculating a calculated fuel supply distribution value corresponding to the minimum value to be maintained; and switching the fuel supply distribution to the calculated fuel distribution value.
-
-
-
-
-
-
-
-
-
Search Results
485
records
(took 0.021 seconds)
