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    DISPOSITIF D'ECHAUFFEMENT D'UN FLUIDE
    51.
    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

    Applicant: SNECMA

    Inventor： VUILLAMY, Didier ,  BARTHOULOT, Jean-Luc ,  SANNINO, Jean-Michel

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

    CPC classification number: 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

    Abstract: 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).

    Combustor for a gas turbine engine
    53.
    发明公开
    Combustor for a gas turbine engine 有权
    Brennkammerfüreine Gasturbinenanlage

    公开(公告)号：EP2169303A2

    公开(公告)日：2010-03-31

    申请号：EP09170923.8

    申请日：2009-09-22

    Applicant: Alstom Technology Ltd

    Inventor： Poyyapakkam, Madhavan Narasimhan

    IPC: F23C6/04 ,  F23R3/00 ,  F23M9/10

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

    Abstract: 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).

    Abstract translation: 本发明涉及一种用于燃气涡轮发动机的燃烧器（1），特别是具有顺序燃烧的燃气轮机。 燃烧器（1）包括限定混合区域（5）和燃烧区域（6）的燃烧器壁（4）。 混合区域（5）包括用于将燃烧空气引入混合区域（5）的至少一个第一入口（2）和用于将燃料引入混合区域（5）的至少一个第二入口，燃烧区域（6）延伸 在混合区域的下游。 在过渡区域（14）中与燃烧区域（6）交叉的混合区域（5）。 挡板9通常在下游方向（15）从过渡区域（14）延伸，形成在燃烧器壁（4）和挡板（9）之间的至少一个空间（10）。

    Fuel nozzle assembly for reduced exhaust emissions
    58.
    发明公开
    Fuel nozzle assembly for reduced exhaust emissions 有权
    用于减少废气排放的燃料喷射器喷嘴组合件

    公开(公告)号：EP1186832A2

    公开(公告)日：2002-03-13

    申请号：EP01307493.5

    申请日：2001-09-04

    Applicant: GENERAL ELECTRIC COMPANY

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

    IPC: F23R3/34

    CPC classification number: F23R3/346 ,  F23C2201/20 ,  F23C2201/401

    Abstract: 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.

    Katalytischer Brenner
    60.
    发明公开
    Katalytischer Brenner 失效

    公开(公告)号：EP0789188A2

    公开(公告)日：1997-08-13

    申请号：EP97101303.2

    申请日：1997-01-29

    Applicant: FRAUNHOFER-GESELLSCHAFT ZUR FÖRDERUNG DER ANGEWANDTEN FORSCHUNG E.V.

    Inventor： Schuler, Alex, Dr.

    IPC: F23C11/00 ,  F23D14/18

    CPC classification number: F23C13/00 ,  F23C6/045 ,  F23C13/02 ,  F23C2201/401 ,  F23M2900/13003 ,  F24H1/0045 ,  F24H2240/00

    Abstract: Die Erfindung betrifft einen (1) katalytischen Brenner mit Brennmittel- und Luftzuführeinrichtungen mit mindestens einem Katalysator (3) und kühlmitteldurchflossenen Wandteilen (4,5), wobei die Wärmeübertragung des ersten Katalysators auf die Wandteile im wesentlichen durch Strahlung erfolgt.

    Abstract translation: 燃烧器具有供应燃料和空气的设备（1），并且具有至少一个催化剂（3）。 它还具有壁部件，冷却剂可以流过。 从第一催化剂到壁部件的热传递主要来自辐射。 组分可以通过空间（2）从第一催化剂分离，燃料和空气的混合物通过该空间在催化剂的方向上流动。 它们还可以通过空间（2a）与第一催化剂分离，燃料和空气的部分燃烧的混合物通过空间沿着大部分不在壁部件（5）上的方向流动。

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