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公开(公告)号：US08240151B2
公开(公告)日：2012-08-14
申请号：US11625539
申请日：2007-01-22
IPC分类号： F02C1/00
CPC分类号： F23D11/107 , F23D11/383 , F23R3/14 , F23R3/283 , F23R2900/00004
摘要： A fuel injector for a gas turbine engine comprises a housing stem and a nozzle, the nozzle including an internal wall in heat transfer relation with fuel flowing through the nozzle, and an external wall in heat transfer relation with ambient air. The internal and external walls have downstream tip ends that are relatively moveable at an interface due to relative thermal growth during operation of the engine. An internal insulating gap is disposed between the internal and external walls to provide a heat shield for the internal wall, and a bellows internal to the injector has an upstream end sealingly attached to an upstream portion of one of the internal and external walls, and a downstream end sealingly attached to a downstream portion of the other wall to fluidly separate the insulating gap from any fuel entering into the nozzle through the interface.
摘要翻译： 一种用于燃气涡轮发动机的燃料喷射器包括壳体杆和喷嘴，喷嘴包括与流过喷嘴的燃料的热传递关系的内壁和与环境空气传热的外壁。 内壁和外壁具有在发动机操作期间由于相对热增长而在界面处相对移动的下游末端。 在内壁和外壁之间设置内部绝缘间隙，以为内壁提供隔热罩，并且喷射器内部的波纹管具有密封地连接到内壁和外壁之一的上游部分的上游端，并且 下游端密封地附接到另一壁的下游部分，以将绝缘间隙与通过界面进入喷嘴的任何燃料流体分离。
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公开(公告)号：US20100300105A1
公开(公告)日：2010-12-02
申请号：US12787470
申请日：2010-05-26
CPC分类号： F23R3/343 , F23D11/103 , F23D2900/11101 , F23R3/14 , F23R3/286
摘要： An airblast fuel nozzle assembly (10) comprising a sleeve structure having a series of coaxial sleeves forming an inner-air circuit, an outer-air circuit, a main-fuel-feed circuit, and a pilot-fuel-feed circuit. The pilot-fuel-feed circuit includes a channel (44), and a discharge region (45) with exits (46). The exits (46) have a combined cross-sectional area that is substantially less than the cross-sectional area of the channel (44) upstream of the discharge region (45). In this manner, the pilot-fuel-feed circuit itself can provide a relatively large pressure drop across the channel region (44), and thereby assist in self atomization during ignition stages of engine operation.
摘要翻译： 一种喷气燃料喷嘴组件（10），包括具有形成内部空气回路的一系列同轴套筒的套筒结构，外部空气回路，主燃料供给回路和先导燃料供给回路。 导向燃料供给回路包括通道（44）和具有出口（46）的排出区域（45）。 出口（46）具有基本上小于放电区域（45）上游的通道（44）的横截面面积的组合横截面面积。 以这种方式，先导燃料供给回路本身可以在通道区域（44）上提供相对较大的压降，从而在发动机运转的点火阶段期间有助于自身雾化。
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公开(公告)号：US20100192585A1
公开(公告)日：2010-08-05
申请号：US12365378
申请日：2009-02-04
IPC分类号： F02M61/02
CPC分类号： B05B7/10 , B05B1/3436 , F02C7/22 , F02C9/40 , F05D2260/85 , F23D11/103 , F23D11/107 , F23D11/383 , F23D17/002 , F23D2206/10 , F23D2900/00015 , F23L7/002 , F23R3/28
摘要： A nozzle assembly (10) comprising a first inlet tube (14), a second inlet tube (15), and a nozzle (16). The nozzle (16) is formed from a stack of plates (20-38) which are joined together in face-to-face contact. The plates (20-38) collectively have openings which define a nozzle outlet, a first inlet, a second inlet, a first circuit from the first inlet to the nozzle outlet, a second circuit from the second inlet to the nozzle outlet, and a fluid-outlet chamber through which both the first circuit and the second circuit pass. The nozzle assembly (10) can be used as a fuel injector for a gas turbine engine, with jet fuel being supplied to the first circuit during start-up and low power conditions and jet fuel being supplied to both the first circuit and the second circuit during high power conditions.
摘要翻译： 一种喷嘴组件（10），包括第一入口管（14），第二入口管（15）和喷嘴（16）。 喷嘴（16）由一堆板（20-38）形成，它们以面对面的接触方式接合在一起。 板（20-38）共同具有开口，其限定喷嘴出口，第一入口，第二入口，从第一入口到喷嘴出口的第一回路，从第二入口到喷嘴出口的第二回路，以及 流体出口室，第一电路和第二电路都通过该室流过。 喷嘴组件（10）可以用作燃气涡轮发动机的燃料喷射器，其中喷射燃料在起动和低功率条件期间被供应到第一回路，喷射燃料被供应到第一回路和第二回路 在高功率条件下。
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4.发明申请公开(公告)号：US20090044538A1
公开(公告)日：2009-02-19
申请号：US12105770
申请日：2008-04-18
IPC分类号： B05B1/24
CPC分类号： F23R3/283 , F23R3/14 , Y02T50/675
摘要： A fuel injector for a gas turbine engine of an aircraft, and more particularly a novel and unique heatshield structure for a fuel nozzle wherein a labyrinth seal is uniquely provided in the nozzle to isolate a portion of an insulating gap from an interface whereat fuel may enter the insulating gap, and the insulating gap is provided with a positive purge flow for forcing vapors out of the insulating gap.
摘要翻译： 一种用于飞行器的燃气涡轮发动机的燃料喷射器，更具体地，一种用于燃料喷嘴的新颖独特的遮光罩结构，其中在喷嘴中独特地设置迷宫式密封，以将绝缘间隙的一部分与燃料可能进入的界面隔离 绝缘间隙和绝缘间隙具有用于迫使蒸气离开绝缘间隙的正净化流。
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公开(公告)号：US5761907A
公开(公告)日：1998-06-09
申请号：US720252
申请日：1996-09-26
申请人： Robert R. Pelletier , Kiran Patwari
发明人： Robert R. Pelletier , Kiran Patwari
CPC分类号： F23D11/107 , F23R3/14 , F23R3/28 , F23D2211/00
摘要： An airblast fuel nozzle has an injector head with an outer air flow through an outer air flow swirler, an intermediate fuel flow through an intermediate fuel swirler, and an inner air flow through an inner air swirler. A heatshield assembly protects the intermediate fuel swirler from hot air passing through the inner air swirler. The heatshield assembly includes an inner heatshield extending from the inlet end of the fuel swirler to the outlet end of the fuel swirler, and an intermediate heatshield disposed between the inner heatshield and the fuel swirler. According to one embodiment, the inner heatshield is connected, such as by brazing, at its downstream end to the intermediate heatshield, and at its upstream end to the fuel swirler. The upstream connection to the fuel swirler is preferably at or downstream from the midpoint of the fuel swirler. An air gap is provided between the inner heatshield and the intermediate heatshield, and between the intermediate heatshield and the fuel swirler. According to a second embodiment, the intermediate heatshield is connected at its downstream end to the downstream end of the fuel swirler, and at its upstream end to the inner heatshield, at a location at or downstream from the midpoint of the inner heatshield. An air gap is also provided between the inner heatshield and the intermediate heatshield, and between the intermediate heatshield and the fuel swirler. The intermediate heatshield allows axial and radial expansion of the inner heatshield without affecting the fluid flow through the fuel passage or the inner air passage, has reduced stress concentration at the connection point, and has increased cycle life without fatigue failure.
摘要翻译： 喷气燃料喷嘴具有喷射头，其具有穿过外部空气流旋流器的外部气流，通过中间燃料旋流器的中间燃料流和通过内部空气旋流器的内部空气流。 挡风玻璃组件保护中间燃料旋流器免受通过内部空气旋流器的热空气。 挡风玻璃组件包括从燃料旋流器的入口端延伸到燃料旋流器的出口端的内部遮光罩，以及设置在内部遮光罩和燃料旋流器之间的中间挡风玻璃。 根据一个实施例，内部遮光罩例如通过钎焊在其下游端连接到中间挡风玻璃，并且在其上游端连接到燃料旋流器。 与燃料旋流器的上游连接优选在燃料旋流器的中点处或下游。 在内部遮光罩和中间挡风板之间以及中间挡风玻璃和燃料旋流器之间设置气隙。 根据第二实施例，中间遮光罩在其下游端连接到燃料旋流器的下游端，并且在其上部端连接到内部遮光罩，在内部遮光罩的中点处或下游的位置。 在内部遮光罩和中间挡风板之间以及中间挡风玻璃和燃料旋流器之间还设有气隙。 中间挡风玻璃允许内部遮光罩的轴向和径向膨胀，而不影响通过燃料通道或内部空气通道的流体流动，在连接点处具有减小的应力集中，并且具有增加的循环寿命而没有疲劳失效。
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公开(公告)号：US20100251720A1
公开(公告)日：2010-10-07
申请号：US11625539
申请日：2007-01-22
IPC分类号： F02C7/22
CPC分类号： F23D11/107 , F23D11/383 , F23R3/14 , F23R3/283 , F23R2900/00004
摘要： A fuel injector for a gas turbine engine comprises a housing stem and a nozzle, the nozzle including an internal wall in heat transfer relation with fuel flowing through the nozzle, and an external wall in heat transfer relation with ambient air. The internal and external walls have downstream tip ends that are relatively moveable at an interface due to relative thermal growth during operation of the engine. An internal insulating gap is disposed between the internal and external walls to provide a heat shield for the internal wall, and a bellows internal to the injector has an upstream end sealingly attached to an upstream portion of one of the internal and external walls, and a downstream end sealingly attached to a downstream portion of the other wall to fluidly separate the insulating gap from any fuel entering into the nozzle through the interface.
摘要翻译： 一种用于燃气涡轮发动机的燃料喷射器包括壳体杆和喷嘴，喷嘴包括与流过喷嘴的燃料的热传递关系的内壁和与环境空气传热的外壁。 内壁和外壁具有在发动机操作期间由于相对热增长而在界面处相对移动的下游末端。 在内壁和外壁之间设置内部绝缘间隙，以为内壁提供隔热罩，并且喷射器内部的波纹管具有密封地连接到内壁和外壁之一的上游部分的上游端，并且 下游端密封地附接到另一壁的下游部分，以将绝缘间隙与通过界面进入喷嘴的任何燃料流体分离。
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公开(公告)号：US20080308654A1
公开(公告)日：2008-12-18
申请号：US12140002
申请日：2008-06-16
IPC分类号： B05B1/34
CPC分类号： F23R3/286 , F23D2213/00 , F23R2900/00018
摘要： A fuel injector nozzle for dispensing fuel in the combustion chamber of a gas turbine engine, comprises a fluid feed conduit having at least one internal channel for the passage of fluid from an inlet end to an outlet end of the fluid feed conduit. The fluid feed conduit has a first annular segment receiving fluid from the inlet end and a second annular segment fluidly connected to receive fluid from the first annular segment at a junction having a circumferential length less than the circumferential lengths of the first and second annular segments. The second annular segment includes fluid dispensing openings to dispense fluid from the conduit, and the first and second annular segments are coaxial and axially separated for relative movement over a major portion of the second segment to accommodate differential thermal expansion.
摘要翻译： 用于在燃气涡轮发动机的燃烧室中分配燃料的燃料喷射器喷嘴包括具有至少一个内部通道的流体供给管道，用于使流体从流体供给导管的入口端到出口端通过。 流体供给管道具有从入口端接收流体的第一环形段和流体连接以在具有小于第一和第二环形段的周向长度的圆周长度的接合处处接收来自第一环形段的流体的第二环形段。 第二环形段包括用于从管道分配流体的流体分配开口，并且第一和第二环形段是同轴的并且轴向分离用于在第二段的主要部分上的相对运动以适应不同的热膨胀。
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公开(公告)号：US08661824B2
公开(公告)日：2014-03-04
申请号：US12787470
申请日：2010-05-26
CPC分类号： F23R3/343 , F23D11/103 , F23D2900/11101 , F23R3/14 , F23R3/286
摘要： An airblast fuel nozzle assembly (10) comprising a sleeve structure having a series of coaxial sleeves forming an inner-air circuit, an outer-air circuit, a main-fuel-feed circuit, and a pilot-fuel-feed circuit. The pilot-fuel-feed circuit includes a channel (44), and a discharge region (45) with exits (46). The exits (46) have a combined cross-sectional area that is substantially less than the cross-sectional area of the channel (44) upstream of the discharge region (45). In this manner, the pilot-fuel-feed circuit itself can provide a relatively large pressure drop across the channel region (44), and thereby assist in self atomization during ignition stages of engine operation.
摘要翻译： 一种喷气燃料喷嘴组件（10），包括具有形成内部空气回路的一系列同轴套筒的套筒结构，外部空气回路，主燃料供给回路和先导燃料供给回路。 导向燃料供给回路包括通道（44）和具有出口（46）的排出区域（45）。 出口（46）具有基本上小于放电区域（45）上游的通道（44）的横截面面积的组合横截面面积。 以这种方式，先导燃料供给回路本身可以在通道区域（44）上提供相对较大的压降，从而在发动机运转的点火阶段期间有助于自身雾化。
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公开(公告)号：US08464539B2
公开(公告)日：2013-06-18
申请号：US12365378
申请日：2009-02-04
CPC分类号： B05B7/10 , B05B1/3436 , F02C7/22 , F02C9/40 , F05D2260/85 , F23D11/103 , F23D11/107 , F23D11/383 , F23D17/002 , F23D2206/10 , F23D2900/00015 , F23L7/002 , F23R3/28
摘要： A nozzle assembly (10) comprising a first inlet tube (14), a second inlet tube (15), and a nozzle (16). The nozzle (16) is formed from a stack of plates (20-38) which are joined together in face-to-face contact. The plates (20-38) collectively have openings which define a nozzle outlet, a first inlet, a second inlet, a first circuit from the first inlet to the nozzle outlet, a second circuit from the second inlet to the nozzle outlet, and a fluid-outlet chamber through which both the first circuit and the second circuit pass. The nozzle assembly (10) can be used as a fuel injector for a gas turbine engine, with jet fuel being supplied to the first circuit during start-up and low power conditions and jet fuel being supplied to both the first circuit and the second circuit during high power conditions.
摘要翻译： 一种喷嘴组件（10），包括第一入口管（14），第二入口管（15）和喷嘴（16）。 喷嘴（16）由一堆板（20-38）形成，它们以面对面的接触方式接合在一起。 板（20-38）共同具有开口，其限定喷嘴出口，第一入口，第二入口，从第一入口到喷嘴出口的第一回路，从第二入口到喷嘴出口的第二回路，以及 流体出口室，第一电路和第二电路都通过该室流过。 喷嘴组件（10）可以用作燃气涡轮发动机的燃料喷射器，其中喷射燃料在起动和低功率条件期间被供应到第一回路，喷射燃料被供应到第一回路和第二回路 在高功率条件下。
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公开(公告)号：US08020384B2
公开(公告)日：2011-09-20
申请号：US12140002
申请日：2008-06-16
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , F23D2213/00 , F23R2900/00018
摘要： A fuel injector nozzle for dispensing fuel in the combustion chamber of a gas turbine engine, comprises a fluid feed conduit having at least one internal channel for the passage of fluid from an inlet end to an outlet end of the fluid feed conduit. The fluid feed conduit has a first annular segment receiving fluid from the inlet end and a second annular segment fluidly connected to receive fluid from the first annular segment at a junction having a circumferential length less than the circumferential lengths of the first and second annular segments. The second annular segment includes fluid dispensing openings to dispense fluid from the conduit, and the first and second annular segments are coaxial and axially separated for relative movement over a major portion of the second segment to accommodate differential thermal expansion.
摘要翻译： 用于在燃气涡轮发动机的燃烧室中分配燃料的燃料喷射器喷嘴包括具有至少一个内部通道的流体供给管道，用于使流体从流体供给导管的入口端到出口端通过。 流体供给管道具有从入口端接收流体的第一环形段和流体连接以在具有小于第一和第二环形段的周向长度的圆周长度的接合处处接收来自第一环形段的流体的第二环形段。 第二环形段包括用于从管道分配流体的流体分配开口，并且第一和第二环形段是同轴的并且轴向分离用于在第二段的主要部分上的相对运动以适应不同的热膨胀。
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