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41. 发明授权

US3175643A Compressor and atomizing nozzle lubricator 失效
标题翻译：压缩机和雾化喷嘴润滑器
公开(公告)号：US3175643A
公开(公告)日：1965-03-30
申请号：US19849862
申请日：1962-05-29
申请人： GULF RESEARCH DEVELOPMENT CO
发明人： DAVIS SR ORVIS A , WALSH BRUCE R
IPC分类号： F16N7/32 , F23D11/10
CPC分类号： F16N7/32 , F23D11/105

42. 发明授权

US3144897A Oil burner apparatus 失效
标题翻译：油燃烧器
公开(公告)号：US3144897A
公开(公告)日：1964-08-18
申请号：US7024560
申请日：1960-11-18
申请人： GULF RESEARCH DEVELOPMENT CO
发明人： ALBERT BIBER , DAVIS SR ORVIS A
IPC分类号： F23D11/10
CPC分类号： F23D11/105 , F23D11/10

43. 发明授权

US3137338A Process and apparatus for burning liquid or gaseous fuel 失效
标题翻译：用于燃烧液体或气体燃料的方法和设备
公开(公告)号：US3137338A
公开(公告)日：1964-06-16
申请号：US2613260
申请日：1960-05-02
申请人： GULF RESEARCH DEVELOPMENT CO
发明人： ALBERT BIBER , WALSH BRUCE R
IPC分类号： F23D11/10
CPC分类号： F23D11/105 , F23D11/10

44. 发明授权

US2861628A Liquid atomisers 失效
标题翻译：液体雾化器
公开(公告)号：US2861628A
公开(公告)日：1958-11-25
申请号：US54613455
申请日：1955-11-10
申请人： FRASER REGINALD P
发明人： FRASER REGINALD P
IPC分类号： B05B7/04 , B05B7/06 , B05B7/10 , F23D11/10
CPC分类号： F23D11/105 , B05B7/0458 , B05B7/066 , B05B7/10

45. 发明授权

US2566040A Fuel burning method and burner 失效
标题翻译：燃油燃烧方法和燃烧器
公开(公告)号：US2566040A
公开(公告)日：1951-08-28
申请号：US77630347
申请日：1947-09-26
申请人： NEW YORK CENTRAL RAILROAD CO
发明人： SIMMONS LAWRENCE C
IPC分类号： F23D11/10
CPC分类号： F23D11/105

46. 发明公开

US20230228415A1 LIQUID FUEL SELF-SUSTAINING COMBUSTION BURNER FOR FLAME SYNTHESIS 审中-公开
公开(公告)号：US20230228415A1
公开(公告)日：2023-07-20
申请号：US17894178
申请日：2022-08-24
申请人： TSINGHUA UNIVERSITY
发明人： SHUI-QING LI , XING JIN , MIN-HANG SONG , YI-YANG ZHANG , ZE-YUN WU , SHU-TING LEI
IPC分类号： F23D11/38 , F23D11/10
CPC分类号： F23D11/383 , F23D11/105 , F23D2202/00
摘要： The present disclosure relates to a liquid fuel self-sustaining combustion burner for flame synthesis, including a swirl-flow cylinder and a stable combustion cylinder. A swirl-flow plate is disposed at an open end of the swirl-flow cylinder and defines swirl-flow outlets. A tangential inlet tube is mounted on the swirl-flow cylinder and in fluid communication with the swirl-flow chamber. An open end of the swirl-flow cylinder extends into the stable combustion chamber. The fuel can be atomized by an atomizer and sprayed into the stable combustion chamber for combustion. Air introduced from the tangential inlet tube can flow into the swirl-flow chamber and advance spirally around the central stabilizing column to reach the swirl-flow plate. The airflow is partially injected into the stable combustion chamber through the swirl-flow outlets, and then continues to spirally advance. An atomizing nozzle of the atomizer is located inside the swirling airflow.

47. 发明申请

US20180306437A1 FUEL SWIRLER WITH ANTI-ROTATION FEATURES 审中-公开
公开(公告)号：US20180306437A1
公开(公告)日：2018-10-25
申请号：US15495043
申请日：2017-04-24
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Peter E. Gunderson
IPC分类号： F23D11/38 , F23R3/28
CPC分类号： F23D11/383 , F05D2230/64 , F05D2240/35 , F05D2260/30 , F23D11/105 , F23D11/107 , F23D14/24 , F23D2900/14021 , F23D2900/14241 , F23R3/002 , F23R3/06 , F23R3/12 , F23R3/14 , F23R3/26 , F23R3/28 , F23R3/283 , F23R3/286 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , Y02T50/675
摘要： A fuel swirler with anti-rotation features is provided. A swirler assembly may comprise a swirler, a guide plate, and a retaining ring. The swirler, the guide plate, and/or the retaining ring may comprise recessions configured to receive a retaining element. The retaining element may be configured to interface with the recessions to create an interference in the swirler assembly. The interference may at least partially resist rotation of the guide plate with respect to the swirler.

48. 发明申请

US20180172275A1 STAGED DUAL FUEL RADIAL NOZZLE WITH RADIAL LIQUID FUEL DISTRIBUTOR 审中-公开
公开(公告)号：US20180172275A1
公开(公告)日：2018-06-21
申请号：US15382112
申请日：2016-12-16
申请人： Delavan Inc
发明人： Lev Alexander Prociw , Jason A. Ryon
IPC分类号： F23R3/28 , F23R3/36
CPC分类号： F23R3/286 , F23D11/10 , F23D11/105 , F23D11/38 , F23D11/383 , F23D14/24 , F23D2900/11101 , F23R3/10 , F23R3/14 , F23R3/346 , F23R3/36 , F23R3/54
摘要： A nozzle includes a nozzle body defining a longitudinal axis and including a primary distributor and a secondary distributor. The primary distributor has an inner air passage fed by a radial swirler; a first fuel circuit radially outboard from the inner air passage with respect to the longitudinal axis; a second fuel circuit radially outboard from the first fuel circuit with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet; and an outer air passage defined between a fuel circuit outer wall and an outer air passage wall, wherein the outer air passage is a converging non-swirling outer air passage. The secondary distributor similar to the primary distributor is downstream of the primary distributor with respect to the longitudinal axis.

49. 发明申请

US20160363321A1 PREFILMING AIR BLAST (PAB) PILOT FOR LOW EMISSIONS COMBUSTORS 有权
标题翻译：用于低排放燃烧器的预热空气（PAB）导向器
公开(公告)号：US20160363321A1
公开(公告)日：2016-12-15
申请号：US14735694
申请日：2015-06-10
申请人： General Electric Company
发明人： Michael Anthony Benjamin , Alfred Albert Mancini , Rameshkumar Muthuvel Chandrasekaran
IPC分类号： F23R3/34
CPC分类号： F23R3/343 , F23D11/104 , F23D11/105 , F23D11/14 , F23D2900/11101 , F23R3/14 , F23R3/32
摘要： A pilot fuel injector is provided for a fuel nozzle of a gas turbine engine. The pilot fuel injector can include an axially-elongated, inner pilot centerbody wall extending from an upstream end to a downstream end, with the axially-elongated, inner pilot centerbody wall having a diverging-converging orientation with respect to a centerline axis to define a hollow tube having an upstream diameter, a throat, and a downstream diameter such that the throat has an inner diameter that is less than both of the upstream diameter and the downstream diameter. The pilot fuel injector also includes a center air circuit positioned at the upstream end, and an annular fuel passage defining the downstream end and intersecting with the centerbody wall at a pilot fuel metering orifice. A pilot fuel film surface is downstream from the annular fuel passage.
摘要翻译：为燃气涡轮发动机的燃料喷嘴设置了先导燃料喷射器。引燃燃料喷射器可以包括从上游端延伸到下游端的轴向细长的内导向中心体壁，其中轴向延伸的内导向中心体壁相对于中心线轴线具有发散会聚方向，以限定中空管具有上游直径，喉部和下游直径，使得喉部具有小于上游直径和下游直径两者的内径。驾驶员燃料喷射器还包括位于上游端的中心空气回路和限定下游端的环形燃料通道，并且在导向燃料计量孔口处与中心体壁相交。导向燃料膜表面在环形燃料通道的下游。

50. 发明授权

US09284933B2 Fuel nozzle with discrete jet inner air swirler 有权
标题翻译：燃油喷嘴与分立的射流内部空气旋流器
公开(公告)号：US09284933B2
公开(公告)日：2016-03-15
申请号：US13782969
申请日：2013-03-01
申请人： Delavan Inc
发明人： Steven Jay Myers
IPC分类号： F02M61/16 , F23R3/14 , F23R3/28 , F23D11/10 , F23D11/38
CPC分类号： F02M61/162 , F23D11/105 , F23D11/386 , F23D2900/00002 , F23R3/14 , F23R3/28
摘要： A fuel nozzle includes an axial fuel circuit having a converging front surface with an axial fuel outlet formed therein, an air swirler surrounding the axial fuel circuit and having a converging front wall, a swirl chamber bounded by the converging front surface of the axial fuel circuit and the converging front wall of the air swirler, and an air cap surrounding the air swirler, such that an air circuit is defined between the air cap and the air swirler. A plurality of circumferentially disposed discrete jet passages extend through the converging front wall of the air swirler for directing atomizing air from the air circuit to the swirl chamber.
摘要翻译：燃料喷嘴包括轴向燃料回路，该轴向燃料回路具有形成在其中的轴向燃料出口的收敛前表面，围绕轴向燃料回路并具有会聚前壁的旋流器，由轴向燃料回路的会聚前表面限定的涡流室以及空气旋流器的会聚前壁和围绕空气旋流器的空气帽，使得在空气帽和空气旋流器之间限定空气回路。多个周向设置的离散喷射通道延伸穿过空气旋流器的会聚前壁，用于将雾化空气从空气回路引导到涡流室。

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