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公开(公告)号：US12066189B2
公开(公告)日：2024-08-20
申请号：US18302943
申请日：2023-04-19
申请人： ROLLS-ROYCE plc
CPC分类号： F23R3/34 , F02C7/228 , F23R3/343 , F23R3/346 , F23R3/60 , F23R2900/00016 , F23R2900/00017 , F23R2900/00018 , F23R2900/00019
摘要： A method of optimising the performance of combustion equipment of a gas turbine engine includes providing a fuel flow into the combustion equipment via a plurality of fuel injectors circumferentially disposed about a principal rotational axis at a plurality of injector positions; determining a plurality of temperatures of combustion gases at a plurality of circumferential positions downstream of the combustion equipment using a plurality of temperature measurement devices; ranking the plurality of circumferential positions based on the plurality of temperatures of the combustion gases determined using the plurality of temperature measurement devices; and repositioning at least some of the plurality of fuel injectors between the plurality of injector positions based at least on the ranking of the circumferential positions.
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公开(公告)号：US12044411B2
公开(公告)日：2024-07-23
申请号：US17350529
申请日：2021-06-17
CPC分类号： F23R3/346 , F02C7/222 , F23R3/46 , F05D2240/35 , F05D2260/201 , F23R2900/03044
摘要： A combustor includes an end cover and at least one fuel nozzle extending from the end cover and at least partially surrounded by a combustion liner. The combustor further includes an outer sleeve spaced apart from and surrounding the combustion liner such that an annulus is defined therebetween. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector that extends through the outer sleeve, the annulus, and the combustion liner to the secondary combustion zone. A fuel supply conduit positioned outside of the outer sleeve. The fuel supply conduit extending to the fuel injector. A shielding assembly coupled to the outer sleeve and at least partially surrounding the fuel supply conduit. The at least one fuel sweep opening is defined in the outer sleeve and disposed within the shielding assembly.
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公开(公告)号：US12044409B2
公开(公告)日：2024-07-23
申请号：US16577537
申请日：2019-09-20
发明人： Lawrence A. Binek , Jesse R. Boyer
CPC分类号： F23R3/283 , B22F5/008 , B22F5/009 , B22F10/38 , F02C7/222 , F23R3/28 , F23R3/346 , B33Y80/00 , F05D2220/80
摘要： An additively manufactured attritable engine includes an engine case, a fuel ring integral and conformal with the engine case, and a fuel manifold attached to the fuel ring and configured to deliver fuel to the fuel ring. The engine also includes a fuel injector attached to the fuel ring and configured to receive fuel from the fuel ring.
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公开(公告)号：US12038178B2
公开(公告)日：2024-07-16
申请号：US18163361
申请日：2023-02-02
发明人： Young Jun Shin , Han Jin Jeong , Eun Seong Cho
摘要： A micro-mixer includes a plurality of fuel tubes through which air and fuel flow, a casing accommodating the plurality of fuel tubes therein, an injection part formed as a pyramidal protrusion on one side of the casing and connected to a front end of the fuel tube to inject the air and the fuel, and a fuel supply divided into a plurality of fuel supply parts to supply the fuel to the fuel tubes.
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公开(公告)号：US12025314B2
公开(公告)日：2024-07-02
申请号：US18147208
申请日：2022-12-28
摘要： A method of operating a combustor of a turbomachine on a total fuel input that contains a concentration of hydrogen that is greater than about 80% is provided. The method includes injecting a first mixture of air and a first fuel containing a first amount of hydrogen into the primary combustion zone of the combustor to generate a first flow of combustion gases having a first temperature. The method further includes injecting, with one or more premix injectors disposed downstream of the fuel nozzles, a second mixture of air and a second fuel containing a second amount of hydrogen into the secondary combustion zone of the combustor to generate a second flow of combustion gases having a second temperature. The method further includes separately injecting a third fuel into secondary combustion zone to generate a third flow of combustion gases having a third temperature.
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公开(公告)号：US12018841B1
公开(公告)日：2024-06-25
申请号：US18211624
申请日：2023-06-20
申请人： ROLLS-ROYCE plc
摘要： A method of operating a gas turbine engine including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also, a gas turbine engine for an aircraft.
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公开(公告)号：US12000346B2
公开(公告)日：2024-06-04
申请号：US18340508
申请日：2023-06-23
申请人： Woodward, Inc.
发明人： Carthel C. Baker , Andrew D. Splitt
CPC分类号： F02C9/263 , F02C7/232 , F02C9/46 , F05D2260/84 , F23R3/346
摘要： A redundant fuel metering system and method for a multi-stage combustor that utilizes a fuel metering valve EHSV from a less critical combustor stage fuel metering system as a redundant backup to the main metering valve EHSV. In the event of a failure of the main FMV EHSV, a control module signals a transfer system to switch control of the main FMV to the less critical combustor stage fuel metering system EHSV, thus maintaining control of the FMV for the main combustor. In doing this, the transfer valve then drives the less critical combustor stage fuel metering system FMV to its failsafe position while maintaining control of the main system.
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公开(公告)号：US20230408098A1
公开(公告)日：2023-12-21
申请号：US17664971
申请日：2022-05-25
摘要： A combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.
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公开(公告)号：US11846426B2
公开(公告)日：2023-12-19
申请号：US17397396
申请日：2021-08-09
摘要： A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.
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公开(公告)号：US20230313995A1
公开(公告)日：2023-10-05
申请号：US17708860
申请日：2022-03-30
发明人： Hatem M. Selim , Baha Suleiman , Majed Sammak , Michael John Hughes , Abdurrahman Abdallah Khalidi , Alaaeldin Elsaeed Dawood
CPC分类号： F23R3/346 , F23R3/36 , F02C3/30 , F02C3/22 , F23R2900/00004 , F05D2240/35
摘要： A method includes delivering fuel and a first portion of oxidant as a rich mixture to the first zone of the combustion chamber. The fuel includes ammonia (NH3). The method further includes burning the rich mixture in the first zone. Combustion gases containing nitrogen oxides (NOx) are produced. The method further includes delivering a second portion of oxidant into the second zone to break down unburned ammonia into ammonia intermediates in the second zone. The nitrogen oxides (NOx) are consumed by reacting with the ammonia intermediates in the second zone. Byproduct hydrogen is produced as a result of breaking down the unburned ammonia into the ammonia intermediates. The method further includes delivering a third portion of oxidant into the third zone. The byproduct hydrogen is burned in the third zone. The third portion of oxidant is greater than the first portion of oxidant and the second portion of oxidant.
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