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1. 发明授权

US10036552B2 Injection system for a combustion chamber of a turbine engine, comprising an annular wall having a convergent inner cross-section 有权
公开(公告)号：US10036552B2
公开(公告)日：2018-07-31
申请号：US14778412
申请日：2014-03-14
申请人： SNECMA , OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES
发明人： Matthieu Francois Rullaud , Didier Hernandez , Christian Guin
IPC分类号： F23R3/34 , F23R3/28 , F23D11/10 , F02C7/22 , F23R3/10
CPC分类号： F23R3/286 , F02C7/22 , F05D2220/30 , F05D2240/35 , F23D11/105 , F23D2206/10 , F23D2900/00015 , F23D2900/11002 , F23R3/10 , F23R3/343 , Y02E20/344
摘要： An air and fuel injection system for a turbine engine combustion chamber dome, including at least two fuel injection devices including a central injector and a peripheral annular injector arranged around the central injector, and an inner annular air inlet channel into which the central injector opens up to enable mixing between the fuel from the central injector and the air inlet into the inner annular channel, and at least one outer annular air inlet channel to enable enrichment of this mix with air and to stabilize the pilot combustion zone, wherein the inner annular channel and at least one outer annular channel are separated by an intermediate annular wall extending around the central injector and having a convergent inner profile.

2. 发明授权

US09927126B2 Prefilming air blast (PAB) pilot for low emissions combustors 有权
公开(公告)号：US09927126B2
公开(公告)日：2018-03-27
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： F23R3/32 , F23R3/34 , F23R3/14 , F23D11/10 , F23D11/14
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.

3. 发明申请

US20170227226A1 LIGHT WEIGHT SWIRLER FOR GAS TURBINE ENGINE COMBUSTOR AND A METHOD FOR LIGHTENING A SWIRLER FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170227226A1
公开(公告)日：2017-08-10
申请号：US15267468
申请日：2016-09-16
申请人： United Technologies Corporation
发明人： Seth A. Max , Jonathan M. Jause
IPC分类号： F23R3/28 , F23R3/14
CPC分类号： F23R3/286 , F23D11/103 , F23D11/105 , F23D11/107 , F23D11/383 , F23D14/24 , F23D2900/14021 , F23D2900/14241 , F23D2900/14701 , F23R3/04 , F23R3/10 , F23R3/12 , F23R3/14 , F23R2900/00017 , F23R2900/00018 , Y02T50/675
摘要： The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.

4. 发明申请

US20160281991A1 INJECTION SYSTEM FOR A COMBUSTION CHAMBER OF A TURBINE ENGINE, COMPRISING AN ANNULAR WALL HAVING A CONVERGENT INNER CROSS-SECTION 有权
标题翻译：涡轮发动机燃烧室喷射系统，包含一个内部交叉部分的环形墙
公开(公告)号：US20160281991A1
公开(公告)日：2016-09-29
申请号：US14778412
申请日：2014-03-14
申请人： SNECMA , OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES
发明人： Matthieu Francois RULLAUD , Didier HERNANDEZ , Christian GUIN
IPC分类号： F23R3/28 , F02C7/22 , F23R3/10
CPC分类号： F23R3/286 , F02C7/22 , F05D2220/30 , F05D2240/35 , F23D11/105 , F23D2206/10 , F23D2900/00015 , F23D2900/11002 , F23R3/10 , F23R3/343 , Y02E20/344
摘要： An air and fuel injection system for a turbine engine combustion chamber dome, including at least two fuel injection devices including a central injector and a peripheral annular injector arranged around the central injector, and an inner annular air inlet channel into which the central injector opens up to enable mixing between the fuel from the central injector and the air inlet into the inner annular channel, and at least one outer annular air inlet channel to enable enrichment of this mix with air and to stabilise the pilot combustion zone, wherein the inner annular channel and at least one outer annular channel are separated by an intermediate annular wall extending around the central injector and having a convergent inner profile.
摘要翻译：一种用于涡轮发动机燃烧室穹顶的空气和燃料喷射系统，包括至少两个燃料喷射装置，包括中心喷射器和围绕中心喷射器设置的外围环形喷射器，以及内部环形空气入口通道，中心喷射器打开以使得能够在来自中心喷射器的燃料和进入内部环形通道的空气入口之间进行混合，以及至少一个外部环形空气入口通道，以使得该混合物能够与空气相融合并稳定先导燃烧区域，其中内部环形通道并且至少一个外环形通道由围绕中心喷射器延伸并具有会聚内轮廓的中间环形壁分开。

5. 发明授权

US09310080B2 Airblast fuel injector 有权
标题翻译：喷气式喷油器
公开(公告)号：US09310080B2
公开(公告)日：2016-04-12
申请号：US14456353
申请日：2014-08-11
申请人： ROLLS-ROYCE PLC
发明人： Ian James Toon
IPC分类号： F02C1/00 , F23R3/14 , F23R3/34 , F23D11/10 , F23R3/28
CPC分类号： F23R3/286 , F23D11/105 , F23D2900/00015 , F23D2900/11101 , F23R3/14 , F23R3/28 , F23R3/343
摘要： An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.
摘要翻译：用于燃气涡轮发动机燃料喷雾喷嘴的喷气燃料喷射器从径向内到外依次具有内部空气旋流器通道，环形燃料通道，环形外部空气旋流器通道和环形外壳空气旋流器的同轴布置通道。喷射器还具有具有内表面轮廓的环形护罩。相对于通过喷射器的整个轴向流动方向，护罩内表面轮廓具有会聚部分，随后是发散部分，其转变形成第一向内指向的环形鼻部。喷射器还具有具有外表面轮廓并具有内表面轮廓的环形壁。相对于通过注射器的整个轴向方向，壁外表面轮廓具有会聚部分，随后是向外转动部分，其面向穿过护罩空气通道到达第一鼻部。

6. 发明授权

US08601818B2 Conical gas turbine burner having a fuel lance with inclined side nozzles 有权
标题翻译：锥形燃气轮机燃烧器具有具有倾斜侧喷嘴的燃料喷枪
公开(公告)号：US08601818B2
公开(公告)日：2013-12-10
申请号：US12684187
申请日：2010-01-08
申请人： Adnan Eroglu
发明人： Adnan Eroglu
IPC分类号： F23R3/28 , F23C5/00 , F02C1/00
CPC分类号： F23R3/34 , F23C6/047 , F23C2900/07002 , F23C2900/07021 , F23D11/105 , F23D11/12 , F23D11/402 , F23D14/58 , F23D14/64 , F23D17/002 , F23D2900/00015 , F23D2900/11101 , F23R3/12 , F23R3/286 , F23R3/343 , F23R3/346 , F23R3/36 , F23R2900/03341
摘要： The burner (1) of a gas turbine includes a swirl generator (2) and, downstream of it, a mixing tube (3). The swirl generator (2) is defined by at least two walls facing one another to define a conical swirl chamber (5) and is provided with nozzles (6) arranged to inject a fuel and apertures (7) arranged to feed an oxidizer into the swirl chamber (5). The burner (1) includes a lance (9) which extends along a longitudinal axis of the swirl generator (2) and is provided with side nozzles (11) for ejecting a fuel within the burner (1). The side nozzles (11) have their axes (12) inclined with respect to the axis of the lance (9) and can be positioned along the axis of the burner.
摘要翻译：燃气轮机的燃烧器（1）包括涡流发生器（2），并在其下游设置有混合管（3）。漩涡发生器（2）由至少两个彼此面对的壁限定，以限定锥形旋流室（5），并且设置有喷嘴（6），其布置成喷射燃料和孔（7），其布置成将氧化剂进料到旋流室（5）。燃烧器（1）包括沿着涡流发生器（2）的纵向轴线延伸的喷枪（9），并且设置有用于在燃烧器（1）内喷射燃料的侧喷嘴（11）。侧喷嘴（11）具有相对于喷枪（9）的轴线倾斜的轴线（12），并且可以沿着燃烧器的轴线定位。

7. 发明申请

US20100304314A1 LOW NOX MIXED INJECTOR 有权
标题翻译：低NOX混合注射器
公开(公告)号：US20100304314A1
公开(公告)日：2010-12-02
申请号：US12599575
申请日：2008-05-06
申请人： Patrice Rouchy , Laurent Garnier , Joseph Vernaz , Carlos Mazzotti De Oliveira
发明人： Patrice Rouchy , Laurent Garnier , Joseph Vernaz , Carlos Mazzotti De Oliveira
IPC分类号： F23D17/00 , C03B5/235
CPC分类号： C03B5/235 , B05B7/066 , F23C5/08 , F23D11/105 , F23D17/002 , F23R3/14 , F23R3/36
摘要： The invention relates to a combustion method for glass melting, in which a flame is created both by a liquid fuel pulse and a single gaseous fuel pulse, characterized in that the fraction of the total power due to the liquid fuel varies between 20 and 80%, and in that the specific gaseous fuel pulse is limited to a value that is sufficiency low so that the NOx content of the flue gases produced does not exceed 800 mg/Sm3 for a cross-fired furnace and 600 mg/Sm3 for an end-fired furnace; an injector for implementing this method; a burner comprising one or more such injectors; a furnace comprising at least one such burner.
摘要翻译：本发明涉及一种用于玻璃熔化的燃烧方法，其中通过液体燃料脉冲和单一气体燃料脉冲产生火焰，其特征在于，由液体燃料引起的总功率的分数在20％和80％之间变化，并且特定气体燃料脉冲被限制为足够低的值，使得所产生的烟道气的NOx含量对于交叉燃烧炉并不超过800mg / Sm 3，而对于终端燃烧炉而言为600mg / 燃烧炉用于实施该方法的喷射器; 包括一个或多个这样的喷射器的燃烧器; 包括至少一个这样的燃烧器的炉子。

8. 发明授权

US3946552A Fuel injection apparatus 失效
标题翻译：燃油喷射装置
公开(公告)号：US3946552A
公开(公告)日：1976-03-30
申请号：US395605
申请日：1973-09-10
申请人： Barry Weinstein , Edward Donald Riley
发明人： Barry Weinstein , Edward Donald Riley
IPC分类号： F23D11/12 , F23D11/10 , F23R3/14 , F02C7/22 , B05B7/10
CPC分类号： F23D11/105 , F23R3/14
摘要： An improved fuel injection apparatus is provided to uniformly disperse a low pressure fuel in a highly atomized manner for introduction into a combustion apparatus. The fuel injection apparatus of this invention employs a system of counter-rotating air swirl means disposed about a shroud member whereby the primary atomizing forces are the high shear stresses developed at the confluence of the counter-rotating air streams and the greater velocity and uniformity at which the fuel is dispersed within the shroud provides for a substantially increased atomization efficiency.
摘要翻译：提供了一种改进的燃料喷射装置，用于以高度雾化的方式均匀地分散低压燃料以引入燃烧装置。本发明的燃料喷射装置采用一个绕旋转罩组件设置的反向旋转的空气涡流装置，其中初级雾化力是在相对旋转空气流的汇合处产生的高剪切应力和较大的速度和均匀度其中燃料分散在护罩内提供了大大提高的雾化效率。

9. 发明授权

US3260461A Process of aspirating and spraying using a swirling fluid jet 失效
标题翻译：使用旋转流体射流吸入和喷雾的过程
公开(公告)号：US3260461A
公开(公告)日：1966-07-12
申请号：US32981063
申请日：1963-12-11
申请人： GULF RESEARCH DEVELOPMENT CO
发明人： ALBERT BIBER , DAVIS SR ORVIS A , WALSH BRUCE R
IPC分类号： F23D11/10
CPC分类号： F23D11/105

10. 发明授权

US3131749A Aspirating liquid fuel burner 失效
标题翻译：吸气液燃料燃烧器
公开(公告)号：US3131749A
公开(公告)日：1964-05-05
申请号：US7022660
申请日：1960-11-18
申请人： GULF RESEARCH DEVELOPMENT CO
发明人： DAVIS SR ORVIS A
IPC分类号： F23C99/00 , F23D11/10
CPC分类号： F23C99/00 , F23C2700/023 , F23D11/10 , F23D11/105

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