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公开(公告)号：EP3336434A1
公开(公告)日：2018-06-20
申请号：EP17207794.3
申请日：2017-12-15
申请人： Delavan, Inc.
CPC分类号： F23R3/286 , F23D11/107 , F23D11/383 , F23D17/002 , F23R3/10 , F23R3/14 , F23R3/346 , F23R3/36
摘要： A nozzle (100) includes a nozzle body (102) defining a longitudinal axis (A). The nozzle body (102) includes an inner air passage (104) having a radial swirler (106) and a converging conical cross-section. A first fuel circuit (108) is radially outboard from the air passage (104) with respect to the longitudinal axis (A). A second fuel circuit (110) is radially outboard from the first fuel circuit (108) with respect to the longitudinal axis (A), wherein each of the first fuel circuit (108) and the second fuel circuit (110) extends from a respective fuel circuit inlet (112, 114) to a respective annular fuel circuit outlet (116, 118). An outer air passage (120) is defined between a fuel circuit outer wall (122) and an outer air passage wall (124), wherein the outer air passage (120) is a converging non-swirling outer air passage.
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公开(公告)号：EP2806217B1
公开(公告)日：2017-12-13
申请号：EP14167277.4
申请日：2014-05-06
CPC分类号： F02C7/22 , F02C3/09 , F23D11/103 , F23D11/107 , F23R3/04 , F23R3/12 , F23R3/14 , F23R3/283
摘要： In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem (310) defining a fuel path for fuel and a flow guide (330) coupled to and extending along the stem. The flow guide receives an air flow (302). The assembly further includes a swirler apparatus (350) coupled to the stem and configured to receive the fuel. The swirler apparatus is further coupled to the flow guide and configured to receive the air flow. The swirler apparatus is configured to mix the fuel and the air flow and direct the mixture into a combustor of the combustor assembly.
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公开(公告)号：EP3076082A1
公开(公告)日：2016-10-05
申请号：EP16163366.4
申请日：2016-03-31
申请人： DELAVAN INC
CPC分类号： F23R3/286 , F23C7/002 , F23C7/004 , F23D11/107 , F23D11/383 , F23R3/12 , F23R3/14 , F23R3/28 , F23R3/283 , F23R3/346
摘要： A nozzle includes a nozzle body defining a longitudinal axis (A). The nozzle body includes an air passage (104) having a radial swirler and a converging conical cross-section. A fuel circuit (106) is radially outboard from the air passage (104) with respect to the longitudinal axis. The fuel circuit (106) extends from a fuel circuit inlet to a fuel circuit annular outlet (110). The fuel circuit (106) includes a plurality of helical passages (112) to mitigate gravitational effects at low fuel flow rates. Each helical passage (112) of the fuel circuit (106) opens tangentially with respect to the fuel circuit annular outlet (110) into an outlet (114) of the air passage (104).
摘要翻译： 喷嘴包括限定纵向轴线（A）的喷嘴体。 喷嘴主体包括具有径向旋流器和会聚锥形横截面的空气通道（104）。 燃料回路（106）相对于纵向轴线从空气通道（104）径向地外侧。 燃料回路（106）从燃料回路入口延伸到燃料回路环形出口（110）。 燃料回路（106）包括多个螺旋通道（112），以在低燃料流率下减轻重力作用。 燃料回路（106）的每个螺旋通道（112）相对于燃料回路环形出口（110）相切地打开成空气通道（104）的出口（114）。
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公开(公告)号：EP2965821A1
公开(公告)日：2016-01-13
申请号：EP15163363.3
申请日：2015-04-13
申请人： Delavan, Inc.
发明人： Myers, Steve , Ryon, Jason , Fogarty, Robert
CPC分类号： F23D11/383 , B05B1/3447 , B05B7/10 , F23D11/107 , F23D11/24 , F23R3/30
摘要： A swirler (104; 200; 302) for inducing swirl on a liquid flow includes a swirler body (130; 314) defining a downstream end (134; 308) and an upstream end (132; 306); a plurality of axial slots (144; 206; 310) on an external surface of the swirler body (130; 314), each of the plurality of axial slots (144; 206; 310) having a slot entrance (150; 202; 312a) and a slot exit (126; 204; 312b); and a slot relief (146) at the slot exit (126; 204; 312b). Each of the plurality of axial slots (144; 206; 310) are helical and configured to impart swirl on the liquid flow as the liquid flow traverses through each of the slots (144; 206; 310).
摘要翻译： 一种用于在液流上引起涡流的旋流器（104; 200; 302），包括限定下游端（134; 308）和上游端（132; 306）的旋流器主体（130; 314） （130; 314）的外表面上的多个轴向狭槽（144; 206; 310），所述多个轴向狭槽（144; 206; 310）中的每一个具有狭槽入口（150; 202; 312a ）和狭槽出口（126; 204; 312b）; 和在狭槽出口（126; 204; 312b）处的狭槽释放部（146）。 多个轴向狭槽（144; 206; 310）中的每一个都是螺旋形的，并且构造成当液体流穿过每个狭槽（144; 206; 310）时在液体流上施加涡流。
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5.发明公开FUEL INJECTOR FOR HIGH ALTITUDE STARTING AND OPERATION OF A GAS TURBINE ENGINE 审中-公开喷油器的燃气涡轮发动机高度相关起动和运转
公开(公告)号：EP2951505A2
公开(公告)日：2015-12-09
申请号：EP14785494.7
申请日：2014-01-30
发明人： CHEN, Daih-Yeou , HU, Xiaolan , PEFFLEY, James , LEE, Hanjie
CPC分类号： F02C7/26 , F23D11/107 , F23D11/24 , F23R3/28 , F23R3/54
摘要： A fuel injector for a combustor of a gas turbine engine includes an air swirler adjacent to a pressure atomizer.
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6.发明公开Systems and methods for cooling a staged airblast fuel injector 审中-公开系统和方法，用于冷却燃料阶梯Druckluftinjektors
公开(公告)号：EP2497922A3
公开(公告)日：2015-06-17
申请号：EP12250054.9
申请日：2012-03-09
申请人： Rolls-Royce plc
发明人： Thomson, Neal
CPC分类号： F23D11/107 , F02C7/2365 , F23D2900/11101 , F23R3/28 , F23R3/343
摘要： The present invention is directed to a staged fuel injector that includes, inter alia , a main fuel circuit for delivering fuel to a main fuel atomizer and a pilot fuel circuit for delivering fuel to a pilot fuel atomizer which is located radially inward of the main fuel atomizer. The main fuel atomizer includes a radially outer prefilmer and a radially inner fuel swirler. Portions of the main fuel circuit are formed in the prefilmer and portions of the pilot fuel circuit are formed in the prefilmer and the fuel swirler and are positioned proximate to and in thermal contact with fuel exit ports associated with the main fuel circuit and formed in the prefilmer. As a result, the pilot fuel circuit cools the stagnant fuel located in main fuel circuit, including the exit ports, even when performing at engine power levels of up to 60% of the maximum take-off thrust.
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公开(公告)号：EP2873923A1
公开(公告)日：2015-05-20
申请号：EP14192874.7
申请日：2014-11-12
IPC分类号： F23R3/28
摘要： A gas turbine combustor (2) comprising a burner (6) including a plurality of fuel nozzles (26) for injecting fuel, and an air hole plate positioned on a downstream side of the fuel nozzles (26). Each of the fuel nozzles and a plurality of air holes (32) are arranged in pairs.
The combustor (2) further comprises a combustion chamber (5) for mixing fuel injected from the fuel nozzles configuring the burner and air injected from the air holes (32) and burning the mixed fuel.
Each of the fuel nozzles (26) is provided with a projection being positioned on a downstream side of a flow of combustion air flowing around each of the fuel nozzles.摘要翻译： 一种燃气轮机燃烧器（2），包括燃烧器（6），其包括用于喷射燃料的多个燃料喷嘴（26）以及位于所述燃料喷嘴（26）的下游侧的气孔板。 每个燃料喷嘴和多个气孔（32）成对布置。 燃烧器（2）还包括用于混合从构成燃烧器的燃料喷嘴喷射的燃料和从空气孔（32）喷射的空气并燃烧混合燃料的燃烧室（5）。 每个燃料喷嘴（26）设置有位于流过每个燃料喷嘴周围的燃烧空气流的下游侧的突起。
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公开(公告)号：EP2589867A3
公开(公告)日：2015-01-07
申请号：EP12191142.4
申请日：2012-11-02
申请人： Delavan Inc.
发明人： Prociw, Lev Alexander , Ryon, Jason
CPC分类号： F23R3/14 , F02C7/22 , F23D11/107 , F23D2900/11101 , F23R3/10 , F23R3/12 , F23R3/28 , F23R3/286 , F23R3/30
摘要： An injector (100) for a multipoint combustor system includes an inner air swirler (102) which defines an interior flow passage (104) and a plurality of swirler inlet ports (106) in an upstream portion thereof. The inlet ports are configured and adapted to impart swirl on flow in the interior flow passage. An outer air cap (110) is mounted outboard of the inner swirler. A fuel passage (112) is defined between the inner air swirler and the outer air cap, and includes a discharge outlet (114)between downstream portions (116, 118) of the inner air swirler and the outer air cap for issuing fuel for combustion. The outer air cap defines an outer air circuit configured for substantially unswirled injection of compressor discharge air outboard of the interior flow passage.
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公开(公告)号：EP2413037A3
公开(公告)日：2014-11-05
申请号：EP11250643.1
申请日：2011-07-11
申请人： Delavan Inc.
CPC分类号： F23R3/286 , F23D11/107 , F23D2900/11101 , F23R3/14 , F23R3/28 , F23R2900/00012 , Y02T50/675 , Y10S239/04
摘要： A nozzle includes an inlet at an upstream end of the nozzle, a discharge outlet at a downstream end of the nozzle, and a fluid delivery passage extending between the inlet and the discharge outlet. Exterior and interior walls of the nozzle have downstream tip ends that are relatively longitudinally movable at one or more interfaces. An internal insulating gap is interposed between the interior and exterior walls to insulate fuel from ambient temperature conditions exterior to the nozzle. One or more flexible seal structures internal to the nozzle isolate a portion of the insulating gap from any ambient fluid entering into the gap through the one or more interfaces while providing relative movement between interior and exterior walls of the nozzle.
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公开(公告)号：EP2778530A1
公开(公告)日：2014-09-17
申请号：EP14158970.5
申请日：2014-03-11
摘要： A combustor (16) comprises an annular combustor chamber formed between inner and outer liners (20, 30). Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes (22, 32) are defined through the inner liner (20) and the outer liner (30) adjacent to and downstream of the fuel nozzles. The nozzle air holes (22, 32) are configured for high pressure air to be injected from an exterior of the liners (20, 30) through the nozzle air holes (22, 32) generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.
摘要翻译： 燃烧器（16）包括形成在内衬和内衬（20,30）之间的环形燃烧室。 燃料喷嘴各自具有与环形燃烧器室流体连通的端部，以在环形燃烧室中注入燃料，燃料喷嘴被定向成沿着具有相对于环形燃烧室的中心轴线的轴向分量的燃料流动方向喷射燃料。 多个喷嘴气孔（22,32）通过内衬（20）和邻近燃料喷嘴下游的外衬（30）而被限定。 喷嘴空气孔（22,32）构造成用于从衬套（20,30）的外部通过喷嘴空气孔（22,32）大体径向地进入环形燃烧室的高压空气。 喷嘴气孔的中心轴线相对于环形燃烧室的中心轴线具有切向分量。
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