公开(公告)号：US06322353B1

公开(公告)日：2001-11-27

申请号：US09397511

申请日：1999-09-17

申请人： Marcel Stalder ,  Günter Sybon

发明人： Marcel Stalder ,  Günter Sybon

IPC分类号： F02C7264

CPC分类号： F02C7/264

摘要： In an ignition appliance for a heat generator, the supply lines for air (70) and fuel gas (60) are led directly into a flame tube (40). The igniter (51) is arranged in an ignition space (50) remote from the flame tube (40) and connected to the flame tube (40). The ignition space (50) is connected to the air supply passage (70) and the gas supply passage (60) via connecting ducts (55, 56). If the supply passages for air and fuel gas (70, 60) are dimensioned so as to be sufficiently large, the pressure drop between the inside of the ignition space (50) and the feed lines (60, 70) is small. The fuel/air ratio present at the igniter (51) is therefore essentially determined only by the ratio of the cross sections of the connecting ducts (55, 56). The flow relationships in the ignition space (50) are likewise substantially decoupled from the air and fuel gas flows supplied overall to the ignition appliance. In consequence, good conditions for a reliable ignition can be set over a wide operating range of the ignition appliance.

摘要翻译： 在用于发热体的点火装置中，将空气供给线（70）和燃料气体（60）直接引导到火焰管（40）中。 点火器51配置在远离火焰管40并与火焰管40连接的点火空间50内。 点火空间（50）通过连接管（55,56）连接到供气通道（70）和气体供应通道（60）。 如果用于空气和燃料气体（70,60）的供应通道的尺寸足够大，则点火空间（50）的内部和进料管线（60,70）之间的压降很小。 因此，在点火器（51）处存在的燃料/空气比基本上仅由连接管道（55,56）的横截面的比率决定。 点火空间（50）中的流动关系同样基本上与整体提供给点火器具的空气和燃料气体流分离。 因此，可以在点火器具的宽的工作范围内设置可靠点火的良好条件。

公开(公告)号：US06729142B2

公开(公告)日：2004-05-04

申请号：US10067284

申请日：2002-02-07

申请人： Marcel Stalder ,  Franz Joos

发明人： Marcel Stalder ,  Franz Joos

IPC分类号： F02C7264

CPC分类号： F02C7/264 ,  F23D2900/00014 ,  F23R3/343

摘要： In a thermal turbomachine with a housing, a combustion chamber, an ignition device, a fuel supply, and an air supply, the ignition device includes an ignition space and an igniter arranged in the ignition space. The fuel supply and the air supply open into the ignition space. The ignition space is connected to the combustion chamber, and the ignition device is arranged outside the housing of the thermal turbomachine. A process is shown for the ignition of the thermal turbomachine outside the housing.

摘要翻译： 在具有壳体，燃烧室，点火装置，燃料供应和空气供应的热涡轮机中，点火装置包括点火空间和布置在点火空间中的点火器。 燃料供应和供气通向点火空间。 点火空间连接到燃烧室，并且点火装置设置在热涡轮机壳体外部。 示出了用于在壳体外部点燃热涡轮机的过程。

公开(公告)号：US06715279B2

公开(公告)日：2004-04-06

申请号：US10090192

申请日：2002-02-04

申请人： Tracy Lowell White

发明人： Tracy Lowell White

IPC分类号： F02C7264

CPC分类号： F23R3/002 ,  F23D2207/00 ,  F23R2900/00012

摘要： An igniter tube for a gas turbine engine combustor has an inner surface, an outer surface, and a longitudinal axis therethrough. More specifically, the igniter tube includes: a first portion positioned within a port of a liner for the combustor, the first portion having an inner surface with an inner diameter and an outer surface with an outer diameter; a second portion located adjacent the first portion, the second portion having an inner surface with an inner diameter and an outer surface with an outer diameter, wherein the second portion outer diameter increases from the first portion outer diameter at a first end to a predetermined outer diameter at a second end; and, a third portion located adjacent the second portion, the third portion having an inner surface with an inner diameter and an outer surface with an outer diameter, wherein the third portion outer diameter is substantially the same as the predetermined outer diameter. Moreover, the second portion inner diameter of the igniter tube is substantially equal to the first portion inner diameter and the third portion inner diameter of the igniter tube is greater than the inner diameter of the second portion.

摘要翻译： 用于燃气涡轮发动机燃烧器的点火管具有内表面，外表面和穿过其的纵向轴线。 更具体地，点火器管包括：位于燃烧器的衬套的端口内的第一部分，第一部分具有内表面和具有外径的外表面; 位于第一部分附近的第二部分，第二部分具有内表面和具有外径的外表面，其中第二部分外径在第一端处从第一部分外径增加到预定外部 直径在第二端; 以及位于第二部分附近的第三部分，第三部分具有内表面和具有外径的外表面的内表面，其中第三部分外径基本上与预定外径相同。 此外，点火管的第二部分内径基本上等于第一部分内径，并且点火管的第三部分内径大于第二部分的内径。

公开(公告)号：US06279310B1

公开(公告)日：2001-08-28

申请号：US09701970

申请日：2000-12-06

申请人： Torsten Strand ,  Leif G. Andersson

发明人： Torsten Strand ,  Leif G. Andersson

IPC分类号： F02C7264

CPC分类号： F02C7/264

摘要： A method for starting a burner device for a gas turbine, where the burner device comprises at least one burner member (5), arranged to be supplied with a liquid fuel, and an ignition member (9), which is activated for igniting a fuel which is supplied to the burner member (5). The fuel which initially is supplied to the burner member (5) and which is ignited by means of the ignition member and generates a burner member flame mainly comprises an ignition gas.

摘要翻译： 一种用于启动用于燃气轮机的燃烧器装置的方法，其中所述燃烧器装置包括布置成供应液体燃料的至少一个燃烧器构件（5），以及点燃构件（9），其被启动以点燃燃料 其被供应到燃烧器构件（5）。 最初被供应到燃烧器构件（5）并且通过点火构件点燃并产生燃烧器构件火焰的燃料主要包括点火气体。

公开(公告)号：US06718773B2

公开(公告)日：2004-04-13

申请号：US10095519

申请日：2002-03-13

申请人： Marcel Stalder ,  Urs Benz ,  Franz Joos ,  Pirmin Schiessel ,  Jaan Hellat ,  Guenter Sybon

发明人： Marcel Stalder ,  Urs Benz ,  Franz Joos ,  Pirmin Schiessel ,  Jaan Hellat ,  Guenter Sybon

IPC分类号： F02C7264

CPC分类号： F23R3/343 ,  F02C7/264 ,  F23D11/404 ,  F23D11/42 ,  F23D17/002 ,  F23D2207/00

摘要： In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber (30), an ignition device (10), a fuel supply (60) and an air supply (70), and the ignition device (10) consisting of an ignition space (50) and of an ignitor (51) arranged in the ignition space (50), the fuel supply (60) and the air supply (70) discharging into the ignition space (50), and the ignition space (50) being connected to the combustion chamber (30) via a flame tube (40), prior to the ignition of the combustion chamber (30), an overall fuel/air mixture ratio &PHgr;overall=1/&lgr;overall greater than 1, with &lgr;overall being the overall air ratio, is set in the flame tube (40) of the ignition device (10).

摘要翻译： 在用于点燃热涡轮机的方法中，包含燃烧室（30），点火装置（10），燃料供应（60）和空气供应（70）的涡轮机和由 点火空间（50）和布置在点火空间（50）中的点火器（51），燃料供应（60）和排放到点火空间（50）中的空气供应（70）和点火空间（50） 在燃烧室（30）点火之前，通过火焰管（40）连接到燃烧室（30），总燃料/空气混合比Phioverall = 1 /λ超过大于1，其中λ为整体 空气比设置在点火装置（10）的火焰管（40）中。

公开(公告)号：US06668557B2

公开(公告)日：2003-12-30

申请号：US10200165

申请日：2002-07-23

申请人： Masataka Ohta ,  Kuniaki Aoyama ,  Mitsuru Inada ,  Shigemi Mandai ,  Satoshi Tanimura ,  Katsunori Tanaka ,  Koichi Nishida

发明人： Masataka Ohta ,  Kuniaki Aoyama ,  Mitsuru Inada ,  Shigemi Mandai ,  Satoshi Tanimura ,  Katsunori Tanaka ,  Koichi Nishida

IPC分类号： F02C7264

CPC分类号： F23R3/20 ,  F23R3/343

摘要： A pilot nozzle of a gas turbine combustor comprises a first structure, provided near a main nozzle of a combustor that injects fuel oil, having a flow channel for a fuel gas and an outlet for the fuel gas. The first structure diffusion-injecting the fuel gas obliquely forward through the outlet to maintain a flame and to aid ignition of the fuel oil injected from the main nozzle. There is further provided a second structure which circulates in whirls a combustion gas generated due to the combustion of the fuel gas.