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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. 发明授权

EP3098429B1 JET ENGINE, FLYING BODY, AND METHOD FOR OPERATING JET ENGINE 有权
公开(公告)号：EP3098429B1
公开(公告)日：2018-12-12
申请号：EP15769123.9
申请日：2015-02-17
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： UENO, Yoshihiko , FURUYA, Shojiro
IPC分类号： F23R3/60
CPC分类号： F23R3/22 , F02C7/042 , F02K7/10 , F02K7/18 , F05D2220/10 , F05D2220/80 , F05D2260/99 , F23R3/60 , F23R2900/00015 , F23R2900/00017 , Y02T50/671
摘要： A jet engine includes an inlet (11) which takes in air and a combustor (12) which combusts fuel with the air. The combustor (12) has an injector (20), a plurality of flame stabilizers (21, 22) and a vanishment section (31). The injector (20) injects the fuel. The plurality of flame stabilizers (21, 22) can maintain the flame (F) used for combustion in the combustor (12). The vanishment section (31) is provided to cover the dent of the first flame stabilizer (21) which is situated on the side near to the inlet in the plurality of flame stabilizers (21, 22), and vanishes with the passage of time in the flight.

6. 发明授权

EP2076714B1 ENERGY RELEASE/CONVERSION DEVICE 有权
标题翻译：能量释放/转换装置
公开(公告)号：EP2076714B1
公开(公告)日：2016-08-31
申请号：EP07854177.8
申请日：2007-10-18
申请人： Lean Flame, INC.
发明人： RAKHMAILOV, Anatoly M.
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23R2900/00015

7. 发明公开

EP2626635A3 Combustor assembly with trapped vortex cavity 有权转让
标题翻译：根据配备涡流空腔燃烧器组件
公开(公告)号：EP2626635A3
公开(公告)日：2013-09-11
申请号：EP13153606.2
申请日：2013-02-01
申请人： General Electric Company
发明人： Boardman, Gregory Allen , Chila, Ronald , McConnaghhay, Johnie F.
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23R2900/00015
摘要： Embodiments of the present application include a combustor assembly (25). The combustor assembly may include an annular trapped vortex cavity (116) located adjacent to a downstream end (106) of a bundle of air/fuel premixing injection tubes (102). The annular trapped vortex cavity (116) may include an opening (124) at a radially inner portion of the annular trapped vortex cavity (116) adjacent to the head end (104) of the bundle of premixing tubes (102). The annular trapped vortex cavity (116) may also include one or more air injection holes (126) and one or more fuel sources (128) disposed about the annular trapped vortex cavity (116) such that the one or more air injection holes (126) and the one or more fuel sources (128) are configured to drive a vortex (130) within the annular trapped vortex cavity (116).

8. 发明公开

EP2475857A1 COMBUSTION CAVITY LAYOUTS FOR FUEL STAGING IN TRAPPED VORTEX COMBUSTORS 审中-公开
标题翻译：用于燃油分离的涡流燃烧室的燃烧室空间
公开(公告)号：EP2475857A1
公开(公告)日：2012-07-18
申请号：EP09849343.0
申请日：2009-11-30
申请人： Lean Flame, Inc.
发明人： KENDRICK, Donald, W.
IPC分类号： F02C1/00
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, alternative combustion cavity layouts are provided for practicing fuel staging in a trapped vortex (TVC) combustion apparatus comprising an inlet premixer, for injecting fuel-air mixture into the inlet of the combustion apparatus and one or more vortex premixers, for injecting fuel-air mixture into the recirculating vortex within each of one or more trapped vortex cavities. A plurality of TVC cavities, may, for example, be laid out axially, radially, peripherally, internally, or in combinations of such arrangements. These layouts may be used in conjunction with a fuel staging method whereby the relative proportion of mixture introduced through the inlet and the respective vortex premixers can be varied as a function of operating conditions.
摘要翻译：在一个实施例中，提供了替代的燃烧室布局，用于在包括入口预混合器的捕集涡流（TVC）燃烧设备中实施燃料分级，用于将燃料空气混合物喷射到燃烧设备的入口和一个或多个涡流预混合器中，燃料 - 空气混合物进入一个或多个驻涡腔中的每一个内的再循环涡流。多个TVC空腔例如可以轴向地，径向地，周边地，内部地或者以这样的布置的组合布置。这些布局可以与燃料分级方法结合使用，其中通过入口引入的混合物和相应涡流预混合器的相对比例可根据操作条件而变化。

9. 发明公开

EP2142777A1 TRAPPED VORTEX COMBUSTION CHAMBER 审中-公开
标题翻译：燃烧室产生涡流被困
公开(公告)号：EP2142777A1
公开(公告)日：2010-01-13
申请号：EP07761677.9
申请日：2007-05-01
申请人： Ingersoll-Rand Energy Systems
发明人： ARMSTRONG, Jeffrey, P. , STAMENOV, Toni, H.
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23L15/04 , F23R3/14 , F23R3/34 , F23R2900/00015 , Y02E20/348
摘要： The combustor consists of a can-type configuration which combusts fuel premixed with air and delivers the hot gases to a turbine. Fuel is premixed with air and is delivered to the combustor with a swirl motion. This swirling mixture of reactants is conveyed through a flowpath that expands, the mixture reacts, and establishes a central recirculation zone. An imperforate trapped vortex cavity is disposed proximal to the swirler apparatus which provides for a second reaction zone. Fresh fuel/air reactants are exchanged with burned products in the trapped vortex and a pilot flame is established in the trapped cavity. The imperforate trapped cavity is not supplied with either fuel or air, but is cooled on a backside of the cavity with a flow of cooling air. The cooling air is then conveyed to the combustion chamber so as to not interfere with the critical flame holding flow features of the combustor.

10. 发明公开

EP1371906A3 Gas turbine engine combustor can with trapped vortex cavity 有权
标题翻译：与空腔的燃气涡轮机燃烧室的圆柱形壳用于产生截留涡流
公开(公告)号：EP1371906A3
公开(公告)日：2007-04-04
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).

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