| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 燃气涡轮发动机的燃料喷嘴及其制造方法 | CN200910004149.6 | 2009-02-12 | CN101509670B | 2012-10-03 | W·K·赫斯勒 |
| 本发明涉及燃气涡轮发动机的燃料喷嘴及其制造方法。具体而言，一种二次燃料喷嘴组件(200)包括喷嘴部分(204)、从该喷嘴部分径向向外延伸的至少一个栓桩(300)以及绕着喷嘴部分在该至少一个栓桩的上游定位的盘(310)，该至少一个栓桩限定了至少一个开孔(304)，该至少一个开孔构造为用以沿大致上游方向引导燃料流，该盘定位为与至少一个开孔成流动连通并构造为干扰燃料流以促进燃料雾化。 | ||||||
| 2 | 用于改变多相射流的特性的设备和方法 | CN200980101941.1 | 2009-01-09 | CN101909761A | 2010-12-08 | B·拉贝戈尔; T·普安索; N·盖泽内克 |
| 本发明涉及一种设备和一种方法，其用于通过多相射流与一股或多股致动射流之间的流体相互作用来喷射具有可变方向和/或开度的多相射流。 | ||||||
| 3 | 燃气涡轮发动机的燃料喷嘴及其制造方法 | CN200910004149.6 | 2009-02-12 | CN101509670A | 2009-08-19 | W·K·赫斯勒 |
| 本发明涉及燃气涡轮发动机的燃料喷嘴及其制造方法。具体而言，一种二次燃料喷嘴组件(200)包括喷嘴部分(204)、从该喷嘴部分径向向外延伸的至少一个栓桩(300)以及绕着喷嘴部分在该至少一个栓桩的上游定位的盘(310)，该至少一个栓桩限定了至少一个开孔(304)，该至少一个开孔构造为用以沿大致上游方向引导燃料流，该盘定位为与至少一个开孔成流动连通并构造为干扰燃料流以促进燃料雾化。 | ||||||
| 4 | 用于改变多相射流的特性的设备和方法 | CN200980101941.1 | 2009-01-09 | CN101909761B | 2013-05-01 | B·拉贝戈尔; T·普安索; N·盖泽内克 |
| 本发明涉及一种设备和一种方法，其用于通过多相射流与一股或多股致动射流之间的流体相互作用来喷射具有可变方向和/或开度的多相射流。 | ||||||
| 5 | 进料喷嘴组件和用于气/液反应的燃烧器设备 | CN200580045972.1 | 2005-12-14 | CN101098750B | 2011-06-15 | 查尔斯·利普 |
| 一种进料喷嘴组件，适于用在涉及气/液反应体系的合成和燃烧反应中，包括多个喷嘴，所述多个喷嘴定位成它们的喷雾彼此撞击，以通过适当平衡液滴的冲击破坏与聚结获得改进的、或维持可接受的、以沙得平均直径形式测量的液滴尺寸。此进料喷嘴组件可以装入到燃烧器设备中，所述燃烧器设备使得环状区与逐渐延伸的挡板结合，用于进料氧气和例如蒸汽的缓和剂气体，环状区和挡板都优选地在例如水套的外部环状冷却装置内。 | ||||||
| 6 | 进料喷嘴组件和用于气/液反应的燃烧器设备 | CN200580045972.1 | 2005-12-14 | CN101098750A | 2008-01-02 | 查尔斯·利普 |
| 一种进料喷嘴组件，适于用在涉及气/液反应体系的合成和燃烧反应中，包括多个喷嘴，所述多个喷嘴定位成它们的喷雾彼此撞击，以通过适当平衡液滴的冲击破坏与聚结获得改进的、或维持可接受的、以沙得平均直径形式测量的液滴尺寸。此进料喷嘴组件可以装入到燃烧器设备中，所述燃烧器设备使得环状区与逐渐延伸的挡板结合，用于进料氧气和例如蒸汽的缓和剂气体，环状区和挡板都优选地在例如水套的外部环状冷却装置内。 | ||||||
| 7 | Supply nozzle assembly and burner apparatus for gas / liquid reaction | JP2007550377 | 2005-12-14 | JP2008526490A | 2008-07-24 | リップ，チャールズ |
| 気体／液体反応系を含む合成反応及び燃焼反応の用途に適した供給ノズル集成体は、液滴の衝撃破壊と凝集とのバランスを好適にとることにより、ザウター平均直径として測定される容認できる液滴の改善を得るか、または維持するためにそれらの噴霧体が互いに衝突するように配置された複数のノズルを含む。 この供給ノズル集成体は、酸素及びモデレータガス、例えば、蒸気を供給するために、段階的に延びるバリヤと組み合わさる環状領域であって、好ましくは全てウォータージャケットのような外部環状冷却手段内にある環状領域をバーナー装置内に内蔵することができる。 | ||||||
| 8 | Swirl impingement prefilming | US14182422 | 2014-02-18 | US10094352B2 | 2018-10-09 | Philip E. O. Buelow; Jason A. Ryon; John E. Short |
| A nozzle for injecting liquid includes a nozzle body defining a plurality of injection point orifices and an annular prefilmer positioned downstream of the injection point orifices for prefilming impingement of spray from the injection point orifices on the prefilmer. A swirl antechamber can be defined upstream of the injection point orifices for supplying a swirling liquid flow to the injection point orifices for impingement of a swirling flow on the prefilmer. | ||||||
| 9 | Burner with lance | US12437223 | 2009-05-07 | US09423125B2 | 2016-08-23 | Richard Carroni; Madhavan Narasimhan Poyyapakkam; Michal Bialkowski; Mark Andrew Willetts |
| The present invention relates to a burner for a combustion chamber of a gas turbine plant. The burner includes a lance for introducing gaseous fuel into the burner. A shaft of the lance has at least one nozzle for introducing gaseous fuel into the burner. A main injection direction of the respective nozzle is oriented onto a portion of a burner wall. An introduction device for a diverting fluid is provided, which is designed for introducing a diverting fluid counteracting an impingement of the fuel flow on the burner wall. | ||||||
| 10 | Systems and Methods Involving Improved Fuel Atomization in Air-Blast Fuel Nozzles of Gas Turbine Engines | US12203383 | 2008-09-03 | US20100050646A1 | 2010-03-04 | Jeffery A. Lovett; Frederick C. Padget; John Mordosky; Shawn M. McMahon |
| Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber defined by an inner surface; and continuously atomizing a portion of the fuel via interaction of the fuel with the inner surface. | ||||||
| 11 | Fuel splashplate for microturbine combustor | US10288013 | 2002-11-05 | US20040083733A1 | 2004-05-06 | Joe Britt Ingram |
| A splashplate dish or disc shaped having a contoured face is inserted in and recessed from the top of the air tube feeding the combustor of a microturbine with a mixture of air and fuel. The splashplate permits the use of a single orifice fuel nozzle or injector to replace a multi orifice injector. The splashplate includes contoured segments circumferentially disposed around the face of the splashplate for splitting the fuel into discrete streams for mixing with the air admitted into the air tube. In one embodiment the splashplate includes radial slots circumferentially spaced around the face of the splashplate for directing the fuel directly into the air tube through the slots. In another embodiment a dimple or depression is located centrally of the splashplate where the fuel impinges before being dispersed in the plurality of streams. Attachment means are provided for centering and recessing the splashplate in the air tube. | ||||||
| 12 | Gas turbine engine combustion apparatus | US634453 | 1984-07-26 | US4561257A | 1985-12-31 | William C. T. Kwan; Anthony Pidcock |
| A gas turbine engine combustion apparatus for vaporizing fuel comprises a flame tube having an upstream end wall in which are located a number of flow guides having associated fuel ducts. In operation, fuel and air flow through the U-shaped duct in each guide and the fuel flows onto the inside of the end wall which acts as a vaporizing surface. The exterior of the end wall is cooled by a flow of air from the engine compressor. The invention avoids the need of vaporizing tubes within the flame tube. | ||||||
| 13 | Spray nozzle, and combustion device having spray nozzle | JP2011003614 | 2011-01-12 | JP2012145026A | 2012-08-02 | OKAZAKI HIROFUMI; KURAMASU KIMIHARU; OKIMOTO HIDEO; ORII AKIHITO; OCHI KENICHI |
| PROBLEM TO BE SOLVED: To promote the combustion reaction, improve the combustion efficiency, and reduce the discharges of soot and dust, carbon monoxide, and nitrogen oxides by reducing the sprayed particle diameters and lowering the kinetic momentum in a combustion device that sprays liquid fuel to combust it.SOLUTION: A spray nozzle has a nozzle plate 22 formed with a groove 28 and a groove 29 worked from an under surface and an upper surface of the nozzle plate 22, respectively. The two grooves crisscross to each other to form a fuel spray hole by being communicated with each other at an intersection part 30. A guide member 23 is contacted to the upstream groove 28 and disposed at a position overlapping the intersection part (fuel spray hole) 30 viewed in the discharge direction of the spray nozzle. The spray fluid (liquid fuel) is branched by the guide member 23 from the fuel flow path 21 connected to the spray nozzle, passes through the upstream groove 28, flows into the intersecting part 30, and is discharged. The spray fluid forms counter flows in the directions toward the intersection part 30 in the upstream groove 28, collide at the obtuse angles of 90° or greater, are sprayed from the intersection part 30, and form a thin fan-like liquid film 31. The liquid film 31 is split apart by the shearing force with respect to the ambient gas to become fine spray particles 32. | ||||||
| 14 | Fuel injector for the combustion chamber of a gas turbine engine | JP2007259471 | 2007-10-03 | JP4930921B2 | 2012-05-16 | ステフアン・トウシヨー; ドウニ・サンドウリ; フランソワ・バンビル |
| 15 | Apparatus and method for changing the characteristics of the multi-phase jet | JP2010541831 | 2009-01-09 | JP2011509183A | 2011-03-24 | グエゼンヌ、ニコラ; ポワンソ、ティエリー; ラベゴール、ベルナール |
| The invention relates to an apparatus and a method for injecting a multiple-phase jet with a variable direction and/or opening, by the fluidic interaction between the multiple-phase jet and one or more actuation jets. | ||||||
| 16 | 噴霧ノズル及び噴霧ノズルを有する燃焼装置 | JP2011003614 | 2011-01-12 | JP5730024B2 | 2015-06-03 | 岡崎 洋文; 倉増 公治; 沖本 英雄; 折井 明仁; 越智 健一 |
| 17 | 多相ジェットの特性を変更する装置及び方法 | JP2010541831 | 2009-01-09 | JP5718055B2 | 2015-05-13 | ラベゴール、ベルナール; ポワンソ、ティエリー; グエゼンヌ、ニコラ |
| 18 | Fuel nozzle for gas turbine engine and method for fabricating the same | JP2009023177 | 2009-02-04 | JP2009192214A | 2009-08-27 | HESSLER WILLIAM KIRK |
| <P>PROBLEM TO BE SOLVED: To provide a secondary fuel nozzle assembly for a gas turbine engine. <P>SOLUTION: The secondary fuel nozzle assembly 200 includes a nozzle 204, and at least one peg 300 extending in a radial outward direction from the nozzle. At least one peg forms at least one opening 304 composed to face a flow of fuel in a substantially upstream direction. The secondary fuel nozzle assembly also includes discs 310 arranged around the nozzle in an upstream of at least one peg, and the disc is arranged in fluid-communication with the at least one opening and constituted to make fuel atomization possible by interfering with the flow of fuel. <P>COPYRIGHT: (C)2009,JPO&INPIT | ||||||
| 19 | Fuel injector for combustion chamber of gas turbine engine | JP2007259471 | 2007-10-03 | JP2008096100A | 2008-04-24 | BAINVILLE FRANCOIS; SANDELIS DENIS; TOUCHAUD STEPHANE |
| PROBLEM TO BE SOLVED: To produce a fuel injector satisfying a criterion concerning the emission of contaminant. SOLUTION: The fuel injector 100 for a combustion chamber of a gas turbine engine comprises a first fuel supply line for operation at an idling speed; a second main fuel supply line for operation at speeds up to full admission; and a first injection orifice 112 and a second injection orifice 113 with which these two fuel supply lines respectively communicate. The injector is configured to arrange the injection orifices 112, 113 in a ring, the first orifice occupying a sector of the ring. COPYRIGHT: (C)2008,JPO&INPIT | ||||||
| 20 | FUEL LANCE WITH MEANS FOR INTERACTING WITH A FLOW OF AIR AND IMPROVE BREAKAGE OF AN EJECTED LIQUID JET OF FUEL | US15525464 | 2014-11-26 | US20170328568A1 | 2017-11-16 | Juan Enrique Portillo Bilbao |
| Apparatus and method for a combustion turbine engine are provided. The apparatus may include a fuel-injecting lance (12) to convey a liquid fuel to a downstream end (16) of the lance. At least one jet in cross-flow injector (18) may be disposed at the downstream end of the lance, and includes an ejection orifice (20) responsive to eject a liquid jet (22) of the fuel. A plurality of surface irregularities (28, 29, 30, 50, 52, 54) is disposed at least on a portion of a wall (32) of the fuel-injecting lance exposed to the flow of air and proximate to the ejection orifice (20). The plurality of surface irregularities may be arranged to interact (e.g., turbulent interaction) with the flow of air to promote breakage of the ejected liquid jet of fuel compared to an injector lacking such surface irregularities. | ||||||
QQ群二维码
意见反馈
意见反馈