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1. 发明公开

EP2475855A4 INLET PREMIXER FOR COMBUSTION APPARATUS 审中-公开
标题翻译：用于燃烧器的进气预混器
公开(公告)号：EP2475855A4
公开(公告)日：2015-04-29
申请号：EP09849340
申请日：2009-11-30
申请人： LEAN FLAME INC
发明人： KENDRICK DONALD W
IPC分类号： F23R3/30 , F02C7/22 , F23C6/04 , F23D14/64 , F23R3/28 , F23R3/34
CPC分类号： F02C7/22 , F05D2250/10 , F05D2250/141 , F23C6/047 , F23D14/64 , F23D2900/14004 , F23R3/286 , F23R3/346 , F23R2900/00015 , Y02E20/14 , Y02E20/16 , Y02E20/18

2. 发明公开

EP2475934A4 VORTEX PREMIXER FOR COMBUSTION APPARATUS 审中-公开
标题翻译：用于燃烧器的涡旋前置器
公开(公告)号：EP2475934A4
公开(公告)日：2015-02-11
申请号：EP09849341
申请日：2009-11-30
申请人： LEAN FLAME INC
发明人： KENDRICK DONALD W
IPC分类号： F23R3/30 , F23R3/28
CPC分类号： F02C7/22 , F05D2250/10 , F05D2250/141 , F23C6/047 , F23D14/64 , F23D2900/14004 , F23R3/286 , F23R3/346 , F23R2900/00015 , Y02E20/14 , Y02E20/16 , Y02E20/18

3. 发明公开

EP2743588A1 Recessed fuel injector positioning 审中-公开
标题翻译：嵌入式喷油器定位
公开(公告)号：EP2743588A1
公开(公告)日：2014-06-18
申请号：EP12196533.9
申请日：2012-12-11
申请人： Siemens Aktiengesellschaft
发明人： Dolmansley, Timothy
IPC分类号： F23R3/34 , F23D11/24 , F23D11/10
CPC分类号： F23R3/343 , F02C7/26 , F02C7/264 , F02C7/266 , F23D11/108 , F23D11/24 , F23D14/02 , F23D2900/00014 , F23Q9/00 , F23R3/12 , F23R3/286 , F23R3/36 , F23R2900/00015
摘要： The present invention relates to a combustion chamber for a gas turbine. The combustion chamber comprises a pilot burner device, a fuel injector (102) and an ignitor unit (103). The pilot burner device comprises a pilot body (100) with a pilot surface (101) which is facing an inner volume of the combustion chamber. The fuel injector (102) comprises a fuel outlet for injecting a fuel into the inner volume. The ignitor unit (103) is adapted for igniting the fuel inside the inner volume, wherein the ignitor unit (103) is arranged at the pilot surface (101) such that fuel which passes the ignitor unit (103) is ignitable. The pilot body (100) comprises a recess (501), wherein the fuel outlet is arranged within the recess (501).
摘要翻译：燃气轮机的燃烧室技术领域本发明涉及燃气轮机的燃烧室。燃烧室包括先导燃烧器装置，燃料喷射器（102）和点火器单元（103）。该引燃器装置包括具有面向燃烧室的内部容积的引导表面（101）的引导主体（100）。燃料喷射器（102）包括用于将燃料喷射到内部容积中的燃料出口。点火器单元（103）适于点燃内部容积内的燃料，其中点火器单元（103）布置在导向表面（101）处，使得通过点火器单元（103）的燃料可点燃。先导主体（100）包括凹部（501），其中燃料出口布置在凹部（501）内。

4. 发明公开

EP1371906A2 Gas turbine engine combustor can with trapped vortex cavity 有权
标题翻译： Gasturbinenbrennkammer mit Hohlraumfüreingeschlossene Wirbel
公开(公告)号：EP1371906A2
公开(公告)日：2003-12-17
申请号：EP03252293.0
申请日：2003-04-10
申请人： GENERAL ELECTRIC COMPANY
发明人： Haynes, Joel Meier , Feitelberg, Alan S. , Burrus, David Louis , Joshi, Narendra Digamber
IPC分类号： F23R3/14 , F23R3/20 , F23R3/28 , F23R3/34
CPC分类号： F23R3/346 , F23C2900/07001 , F23D2900/14004 , F23R3/283 , F23R3/286 , F23R3/58 , F23R2900/00015
摘要： A gas turbine engine combustor can (23) downstream of a pre-mixer (28) has a pre-mixer flowpath (134) therein and circumferentially spaced apart swirling vanes (32) disposed across the pre-mixer flowpath (134). A primary fuel injector (68) is positioned for injecting fuel into the pre-mixer flowpath (134). A combustion chamber (26) is surrounded by an annular combustor liner (27) disposed in supply flow communication with the pre-mixer (28). An annular trapped dual vortex cavity (40) located at an upstream end (30) of the combustor liner (27) is defined between an annular aft wall (44), an annular forward wall (46), and a circular radially outer wall (48) formed therebetween. A cavity opening (42) at a radially inner end (39) of the cavity (40) is spaced apart from the radially outer wall (48). Air injection first holes (112) are disposed through the forward wall (46) and air injection second holes are disposed through the aft wall (44). Fuel injection holes (70) are disposed through at least one of the forward and aft walls (46, 44).
摘要翻译：在预混合器（28）下游的燃气涡轮发动机燃烧室（23）在其中具有预混合器流动路径（134），并且跨过预混合器流动路径（134）设置周向间隔开的涡流叶片（32）。主燃料喷射器（68）被定位成用于将燃料喷射到预混合器流路（134）中。燃烧室（26）被设置成与预混合器（28）供应流动连通的环形燃烧器衬套（27）包围。位于燃烧器衬套（27）的上游端（30）处的环形捕获双涡流腔（40）被限定在环形后壁（44），环形前壁（46）和圆形径向外壁 48）。在空腔（40）的径向内端（39）处的空腔开口（42）与径向外壁（48）间隔开。空气注入第一孔（112）穿过前壁（46）设置，空气注入第二孔穿过后壁（44）设置。燃料喷射孔（70）穿过前壁和后壁（46,44）中的至少一个设置。

5. 发明公开

EP3396146A1 JET ENGINE, FLYING OBJECT, AND OPERATION METHOD FOR JET ENGINE 有权
公开(公告)号：EP3396146A1
公开(公告)日：2018-10-31
申请号：EP16894475.9
申请日：2016-06-22
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： HIROKANE, Mariko , ANDO, Keisuke , UENO, Yoshihiko
IPC分类号： F02K7/10 , F02C7/00 , F02C7/26
CPC分类号： F02K7/10 , F02C7/00 , F02C7/057 , F02C7/26 , F05D2210/33 , F05D2220/10 , F05D2240/35 , F05D2250/51 , F05D2270/3061 , F23R3/10 , F23R3/20 , F23R3/22 , F23R3/28 , F23R2900/00015
摘要： A jet engine is provided with an inlet 11 for taking in air, and a combustor 12 that has a fuel injection port 30a for injecting fuel. The combustor 12 uses the air to combust the fuel injected from the fuel injection port 30a. Between the fuel injection port 30a and the rear end 15 of the inlet, the combustor 12 has a separation part 14 that defines an air flow path FA, through which air flows. A plurality of turbulence generating parts (20, 25) that cause the flow of air to be turbulent are disposed on the separation part 14. Each of the turbulence generating parts (20, 25) includes a member (21, 22, 25B) that, by moving or disappearing, can inhibit the turbulence of the flow of air. A drop in the thrust of the jet engine resulting from a high-pressure region reaching the inlet can thus be prevented.

6. 发明公开

EP3099979A1 COMBUSTOR WITH STAGED, AXIALLY OFFSET COMBUSTION 有权转让
标题翻译：燃烧室梯状，轴向偏差BURNS
公开(公告)号：EP3099979A1
公开(公告)日：2016-12-07
申请号：EP15701653.6
申请日：2015-01-14
申请人： Woodward, Inc.
发明人： LEE, Fei Philip
IPC分类号： F23R3/10 , F23R3/14 , F23R3/26 , F23C7/00
CPC分类号： F23R3/346 , F02C3/04 , F05D2220/32 , F05D2240/35 , F23C7/002 , F23C7/004 , F23R3/10 , F23R3/12 , F23R3/14 , F23R3/26 , F23R3/286 , F23R3/46 , F23R2900/00015
摘要： In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage therethrough having an outlet in a first plane. A second fuel/air mixer assembly comprises a second fuel injector and a plurality of second mixer elements, and each second mixer element defines an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.

7. 发明公开

EP2735799A2 Turbomachine with trapped vortex combustor 审中-公开
标题翻译： Turbomaschine mit einer einem eingeschlossenen Wirbel aufweisenden Verbrennungkammer
公开(公告)号：EP2735799A2
公开(公告)日：2014-05-28
申请号：EP13191880.7
申请日：2013-11-07
申请人： General Electric Company
发明人： Stoia, Lucas John , Romig, Bryan Wesley
IPC分类号： F23R3/20 , F23R3/28 , F23R3/34
CPC分类号： F23R3/28 , F23R3/20 , F23R3/286 , F23R3/346 , F23R2900/00015 , F23R2900/03041
摘要： A turbomachine (10) with a trapped vortex feature (41) includes a unibody liner (30) formed to define a flow path (510) for combustion products, the unibody liner (30) including first and second portions (401, 402) defining first radial planes, a third portion (403) defining a second radial plane and fourth and fifth portions (404, 405) extending substantially radially between proximal ends of the first and third portions (401, 403) and proximal ends of the second and third portions (402, 403), respectively, and an injector (50) configured to deliver a fuel or a fuel/air mixture to a space partially bound by the third, fourth and fifth portions (403, 404, 405).
摘要翻译：具有被捕获的涡流特征（41）的涡轮机（10）包括形成为限定用于燃烧产物的流动路径（510）的单体衬套（30），所述单体衬套（30）包括第一和第二部分（401,402）第一径向平面，限定第二径向平面的第三部分（403）和在第一和第三部分（401,403）的近端和第二和第三部分（401,403）的近端之间大体径向延伸的第四和第五部分（404,405）以及喷射器（50），其配置成将燃料或燃料/空气混合物输送到由第三，第四和第五部分（403,404,405）部分地限定的空间。

8. 发明公开

EP2532965A2 Fuel nozzle with swirling vanes 审中-公开
标题翻译： Kraftstoffdüsemit Wirbelblechen
公开(公告)号：EP2532965A2
公开(公告)日：2012-12-12
申请号：EP12170431.6
申请日：2012-06-01
申请人： General Electric Company
发明人： Romig, Bryan Wesley
IPC分类号： F23R3/14 , F23R3/28 , F23R3/16
CPC分类号： F23R3/14 , F23D2900/14004 , F23D2900/14701 , F23R3/16 , F23R3/286 , F23R2900/00015
摘要： A fuel nozzle (102) includes a swirler (110) and a fuel injector positioned upstream from the swirler (110). The swirler (110) includes an inner hub, an intermediate dividing wall (116), an outer shroud, a number of inner swirling vanes (112), and a number of outer swirling vanes (114). The intermediate dividing wall (116) is concentrically positioned about the inner hub. The outer shroud is concentrically positioned about the intermediate dividing wall (116). Each inner swirling vane (112) extends between the inner hub and the intermediate dividing wall (116), and each outer swirling vane (114) extends between the intermediate dividing (116) wall and the outer shroud.
摘要翻译：燃料喷嘴（102）包括旋流器（110）和位于旋流器（110）上游的燃料喷射器。旋流器（110）包括内轮毂，中间分隔壁（116），外护罩，多个内旋涡叶片（112）和多个外旋涡叶片（114）。中间隔壁（116）围绕内毂同心地定位。外护罩围绕中间分隔壁（116）同心定位。每个内旋涡叶片（112）在内轮毂和中间分隔壁（116）之间延伸，并且每个外旋涡叶片（114）在中间分隔（116）壁和外护罩之间延伸。

9. 发明公开

EP2475934A1 VORTEX PREMIXER FOR COMBUSTION APPARATUS 审中-公开
标题翻译：用于燃烧装置的涡旋前置器
公开(公告)号：EP2475934A1
公开(公告)日：2012-07-18
申请号：EP09849341.4
申请日：2009-11-30
申请人： Lean Flame, Inc.
发明人： KENDRICK, Donald, W.
IPC分类号： F23R3/30
CPC分类号： F02C7/22 , F05D2250/10 , F05D2250/141 , F23C6/047 , F23D14/64 , F23D2900/14004 , F23R3/286 , F23R3/346 , F23R2900/00015 , Y02E20/14 , Y02E20/16 , Y02E20/18
摘要： In one embodiment, a premixer is provided for use, e.g., with trapped vortex (TVC) combustors, that injects premixed fuel and air directly into the recirculating vortex, in a manner compatible with natural vortex flow in the cavity.
摘要翻译：在一个实施例中，预混合器被提供用于例如与捕集涡流（TVC）燃烧器一起使用，该预混合器以与空腔中的自然涡流相兼容的方式将预混燃料和空气直接喷射到再循环涡流中。

10. 发明公开

EP2427694A1 VORTEX COMBUSTOR FOR LOW NOX EMISSIONS WHEN BURNING LEAN PREMIXED HIGH HYDROGEN CONTENT FUEL 审中-公开
标题翻译：涡燃烧室在燃烧贫预混燃料NOX低排放的氢含量高
公开(公告)号：EP2427694A1
公开(公告)日：2012-03-14
申请号：EP09789645.0
申请日：2009-05-06
申请人： Ramgen Power Systems, LLC
发明人： STEELE, Robert, C. , EDMONDS, Ryan, G. , WILLIAMS, Joseph, T. , BALDWIN, Stephen, P.
IPC分类号： F23C9/00 , F23R3/18 , F23R3/20 , F23R3/34 , F23R3/42
CPC分类号： F23C9/006 , F02C3/28 , F05D2220/722 , F23R3/18 , F23R3/20 , F23R3/343 , F23R3/42 , F23R2900/00002 , F23R2900/00015 , F23R2900/03282 , Y02E20/16 , Y02E20/18
摘要： A trapped vortex combustor. The trapped vortex combustor is configured for receiving a lean premixed gaseous fuel and oxidant stream at a velocity which significantly exceeds combustion flame speed in a selected lean premixed fuel and oxidant mixture, thus allowing use of high hydrogen content fuels. The combustor is configured to operate at relatively high bulk fluid velocities while maintaining stable combustion and low NOx emissions. The combustor is useful in gas turbines in a process of burning synfuels, as it offers the opportunity to avoid use of diluent gas to reduce combustion temperatures. The combustor also offers the possibility of avoiding the use of selected catalytic reaction units for removal of oxides of nitrogen from combustion gases exiting a gas turbine.

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