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18 条记录 (耗时 0.007 秒)

    A HYBRID HOMOGENOUS-CATALYTIC COMBUSTION SYSTEM
    1.
    发明公开
    A HYBRID HOMOGENOUS-CATALYTIC COMBUSTION SYSTEM 审中-公开
    混合均相催化燃烧系统

    公开(公告)号：EP3161380A1

    公开(公告)日：2017-05-03

    申请号：EP15744680.8

    申请日：2015-06-26

    申请人： Tubitak

    发明人： KORKMAZ, Özgür Can ,  SARIOGLAN, Alper ,  AKGÜN, Fehmi ,  SAGLAM, Gaye ,  ÇAMKERTEN, Hüseyin ,  AKAR, Egemen ,  SUCU, Yildiz

    IPC分类号： F23C6/04 ,  F23C13/06

    CPC分类号： F23C13/06 ,  F23C6/04 ,  F23C6/042 ,  F23C2201/401 ,  F24H1/0045 ,  F24H1/124 ,  F24H1/40

    摘要： The present invention relates to a hybrid combustion system (1) wherein rich homogeneous combustion and lean catalytic combustion are carried out consecutively, which results in zero NOx emission and is used for obtaining domestic hot water. The present invention relates to a combustion system wherein two serially connected heat exchangers units, which are located in the outlets of the rich homogeneous combustion unit and the lean catalytic combustion unit, transfers the heat generated during combustion reactions into domestic radiator heating water and/or tap water for hot water generation.

    摘要翻译： 本发明涉及一种混合燃烧系统（1），其中连续进行浓均质燃烧和贫催化燃烧，这导致零NOx排放并用于获得生活热水。 本发明涉及一种燃烧系统，其中位于富燃均质燃烧装置和贫燃催化燃烧装置的出口处的两个串联连接的热交换器装置将燃烧反应期间产生的热量传递到家用辐射器加热水中和/或 自来水产生热水。

    COMBUSTOR WITH HEAT EXCHANGER
    3.
    发明公开
    COMBUSTOR WITH HEAT EXCHANGER 审中-公开

    公开(公告)号：EP3418638A1

    公开(公告)日：2018-12-26

    申请号：EP17177065.4

    申请日：2017-06-21

    申请人： General Electric Company

    发明人： BOLANOS, Felipe ,  BIAGIOLI, Fernando ,  WIND, Torsten

    IPC分类号： F23R3/00 ,  F23R3/14 ,  F23R3/18 ,  F23R3/34

    CPC分类号： F23R3/346 ,  F23C2201/401 ,  F23R3/005 ,  F23R3/14 ,  F23R3/18 ,  F23R2900/03341

    摘要： A combustor (16) for a turbomachine includes a rich combustion zone (41) and a low temperature zone (43) downstream of the rich combustion zone. A heat exchanger (100) is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.

    Fuel nozzle assembly for reduced exhaust emissions
    7.
    发明公开
    Fuel nozzle assembly for reduced exhaust emissions 有权
    燃油喷嘴组件可减少废气排放

    公开(公告)号：EP1186832A3

    公开(公告)日：2002-04-24

    申请号：EP01307493.5

    申请日：2001-09-04

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Hura, Harjit Singh ,  Cooper, James Neil ,  Mongia, Hukam Chand ,  Sabla, Paul Edward ,  Duncan, Beverly Stephenson ,  Lohmueller, Steven Joseph

    IPC分类号： F23R3/34

    CPC分类号： F23R3/346 ,  F23C2201/20 ,  F23C2201/401

    摘要： A two-stage fuel nozzle assembly (56) for a gas turbine engine. The primary combustion region (120) is centrally positioned and includes a fuel injector (122) that is surrounded by one or more swirl chambers (132, 160) to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing (168) that surrounds the primary combustion region (120) and it includes a secondary fuel injector (126) having a radially-outwardly-directed opening (172) and surrounded by an annular ring (128) that includes openings (194) for providing a swirl chamber for the secondary combustion region (124). Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region (120) is activated during idle and low engine power conditions, and both the primary (120) and secondary (124) combustion regions are activated during high engine power conditions.

    摘要翻译： 一种用于燃气涡轮发动机的两级燃料喷嘴组件（56）。 主燃烧区域（120）位于中央，并且包括被一个或多个涡流室（132,160）包围的燃料喷射器（122），以提供被点燃以限定第一阶段燃烧区域的燃料空气混合物。 二次燃烧区域由围绕主燃烧区域（120）的环形壳体（168）提供，并且其包括具有径向向外指向的开口（172）并且被环形圈（120）包围的次级燃料喷射器（126） 128），其包括用于为所述第二燃烧区域（124）提供涡流室的开口（194）。 冷却空气在初级燃烧区和次级燃烧区之间有角度地引导，以延迟混合，从而允许相应区在更下游的聚结之前更完全地燃烧。 在怠速和低发动机功率状态期间主燃烧区域（120）被激活，并且在高发动机功率状态期间主燃烧区域（120）和次燃烧区域（124）都被激活。

    Combustor for a gas turbine engine
    8.
    发明公开
    Combustor for a gas turbine engine 有权
    燃烧器用于燃气涡轮植物

    公开(公告)号：EP2169303A3

    公开(公告)日：2014-12-24

    申请号：EP09170923.8

    申请日：2009-09-22

    申请人： ALSTOM Technology Ltd

    发明人： Poyyapakkam, Madhavan Narasimhan

    IPC分类号： F23C6/04 ,  F23R3/00 ,  F23M9/10 ,  F23R3/34

    CPC分类号： F23C6/04 ,  F23C2201/401 ,  F23C2900/06041 ,  F23C2900/07002 ,  F23M9/10 ,  F23R3/00 ,  F23R3/346 ,  F23R2900/03041 ,  F23R2900/03341

    摘要： The invention relates to a combustor (1) for a gas turbine engine, particularly for a gas turbine having sequential combustion. The combustor (1) comprises a combustor wall (4) defining a mixing region (5) and a combustion region (6). The mixing region (5) comprises at least one first inlet (2) for introducing combustion air into the mixing region (5) and at least one second inlet for introducing fuel into the mixing region (5), the combustion region (6) extending downstream of the mixing region. The mixing region (5) crossing over to the combustion region (6) in a transition region (14).
    A baffle (9) extends from the transition region (14) generally in the downstream direction (15) forming at least one space (10) between the combustor wall (4) and the baffle (9).

    DISPOSITIF D'ECHAUFFEMENT D'UN FLUIDE
    9.
    发明公开
    DISPOSITIF D'ECHAUFFEMENT D'UN FLUIDE 审中-公开
    装置用于加热流体

    公开(公告)号：EP2766662A1

    公开(公告)日：2014-08-20

    申请号：EP12781375.6

    申请日：2012-10-09

    申请人： SNECMA

    发明人： VUILLAMY, Didier ,  BARTHOULOT, Jean-Luc ,  SANNINO, Jean-Michel

    IPC分类号： F23C6/04 ,  F28D7/06 ,  F28F9/22

    CPC分类号： F02K9/50 ,  F02K9/60 ,  F23C6/04 ,  F23C2201/40 ,  F23C2201/401 ,  F23C2900/06041 ,  F28D7/00 ,  F28D7/06 ,  F28D7/1615 ,  F28D2021/0026 ,  F28F1/16 ,  F28F1/36 ,  F28F9/22

    摘要： Device for heating a fluid that can be used notably in a rocket launcher to pressurize a liquefied rocket fuel. According to the invention, this device comprises a first burner (21) that performs a first combustion between a limiting rocket fuel (L1) and an excess of rocket fuel (E), and a first exchanger unit (10, 31) in which first burnt gases (B1) emanating from said first combustion give up heat to the fluid (F); it further comprises at least one second burner (22) into which the first burnt gases (B1) on the one hand, and limiting rocket fuel (L2) on the other are injected in order to perform a second combustion between the limiting rocket fuel (L2) and at least some of the unburnt excess rocket fuel present in the first burnt gases (B1); the second burnt gases (B2) emanating from said second combustion flow through a second exchanger unit (10, 32) to give up heat to the fluid (F); the burnt gases (B1, B2) emanating from each of the combustions flow through tubes for burnt gases (31, 32) within the same overall exchanger (10) made up of said exchanger units (10, 31, 32) in which overall exchanger they give up heat to the fluid (F), this fluid flowing between the tubes for burnt gases (31, 32).