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    Combustor turbine interface
    11.
    发明公开
    Combustor turbine interface 有权
    Brennkammer-Turbinen-Übergang

    公开(公告)号：EP1801356A2

    公开(公告)日：2007-06-27

    申请号：EP06256373.9

    申请日：2006-12-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Burd, Steven W.

    IPC: F01D9/02

    CPC classification number: F01D9/023 ,  F05D2240/35 ,  F23R3/50

    Abstract: A combustor assembly (14) for a turbine engine includes an aft open end (24) that communicates gas flow to a turbine assembly (18). The combustor assembly (14) includes a liner assembly (15) that terminates at a first fixed vane (18). A portion of the liner assembly extends an axial distance (37) into the first fixed vane portion (18). An inner surface (42) of the liner assembly (15) corresponds with inner surfaces (45) of the fixed vane portion (18) to provide a smooth transition from the inner surfaces (42) of the combustor assembly (14) to the turbine assembly (18).

    Abstract translation: 用于涡轮发动机的燃烧器组件（14）包括将气流传递到涡轮机组件（18）的后开口端（24）。 燃烧器组件（14）包括终止于第一固定叶片（18）的衬套组件（15）。 衬套组件的一部分将轴向距离（37）延伸到第一固定叶片部分（18）中。 衬套组件（15）的内表面（42）对应于固定叶片部分（18）的内表面（45），以提供从燃烧器组件（14）的内表面（42）到涡轮机 组件（18）。

    Heatshielded article
    12.
    发明公开
    Heatshielded article 审中-公开
    防热物品

    公开(公告)号：EP1617146A2

    公开(公告)日：2006-01-18

    申请号：EP05254335.2

    申请日：2005-07-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Burd, Steven W.

    IPC: F23R3/00 ,  F23M5/08

    CPC classification number: F23R3/002 ,  F23M5/085 ,  F23M2900/05001 ,  F23M2900/05004 ,  F23R2900/03042 ,  F23R2900/03044

    Abstract: A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated cold side 32. A projection projects from an origin 36 at the shield portion to a terminus 38 remote from the shield portion. The terminus includes a protective coating 64 along at least a portion of its length.

    Abstract translation: 防热制品包括支撑件18和固定在支撑件附近的至少一个防热罩20。 防热罩包括与支撑件隔开的防护部分28。 屏蔽部分包括热侧30和未涂覆的冷侧32.突起从屏蔽部分处的原点36突出到远离屏蔽部分的终端38。 末端沿着其长度的至少一部分包括保护涂层64。

    Combustor
    13.
    发明公开
    Combustor 有权
    Brennkammer

    公开(公告)号：EP1522792A1

    公开(公告)日：2005-04-13

    申请号：EP04256235.5

    申请日：2004-10-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Burd, Steven W. ,  Cheung, Albert K. ,  Segalman, Irving ,  Ols, John T. ,  Smith, Reid D.C.

    IPC: F23R3/00 ,  F23R3/42

    CPC classification number: F23R3/002 ,  F23R3/42

    Abstract: A gas turbine engine combustor (20) has inboard and outboard walls (32,134). A forward bulkhead (36) extends between the walls and cooperates therewith to define a combustor interior volume. In longitudinal section, a first portion (54) of the combustor interior volume converges from fore to aft and a second portion (56), aft of the first portion (54) converges from fore to aft more gradually than the first portion (54).

    Abstract translation: 燃气涡轮发动机燃烧器（20）具有内侧和外侧壁（32,134）。 前隔板（36）在壁之间延伸并与其配合以限定燃烧室内部容积。 在纵向截面中，燃烧器内部体积的第一部分（54）从前部向后收缩，并且第一部分（54）的后部的第二部分（56）比第一部分（54）更加逐渐地从前部向后方会聚， 。

    Combustor cooling hole pattern
    18.
    发明公开
    Combustor cooling hole pattern 有权
    Konfiguration derKühlungsbohrungeneiner Brennkammer

    公开(公告)号：EP1705426A1

    公开(公告)日：2006-09-27

    申请号：EP06251068.0

    申请日：2006-02-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Burd, Steven W. ,  Cheung, Albert K.

    IPC: F23R3/00 ,  F23R3/06

    CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042

    Abstract: A combustor assembly (10) includes an inner and outer liner (16,18) defining a combustion chamber (22). The inner and outer liners (16,18) include a plurality of cooling holes (36) spaced a specified distance apart. The cooling holes (36) include first, second and third groups (44,46,48). The first group (44) of cooling holes (36) is the most densely spaced, followed by the second group (46) and then the third group (48). The first group (44) of cooling holes (36) begin upstream of a leading edge (50) of a large opening (50) and terminates downstream of the leading edge (50). The increased density of cooling holes (36) adjacent the large openings (38) provide increased cooling airflow in areas where cooling may be affected by local disturbances in cooling airflow.

    Abstract translation: 燃烧器组件（10）包括限定燃烧室（22）的内部和外部衬套（16,18）。 内衬和内衬（16,18）包括间隔开特定距离的多个冷却孔（36）。 冷却孔（36）包括第一组，第二组和第三组（44,46,48）。 冷却孔（36）的第一组（44）是最密集间隔的，随后是第二组（46），然后是第三组（48）。 冷却孔（36）的第一组（44）从大开口（50）的前缘（50）的上游开始并终止于前缘（50）的下游。 与大开口（38）相邻的冷却孔（36）的增加的密度在冷却可能受到冷却气流中的局部干扰的影响的区域中提供增加的冷却气流。

    Combustor
    19.
    发明公开
    Combustor 有权
    HitzeschildziegelfürBrennkammer

    公开(公告)号：EP1503144A1

    公开(公告)日：2005-02-02

    申请号：EP04254478.3

    申请日：2004-07-27

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Burd, Steven W.

    IPC: F23R3/00

    CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R2900/03042 ,  F23R2900/03044

    Abstract: A combustor heat shield panel (28) is secured relative to a combustor shell (22) so as to hold the panel exterior surface (34) spaced apart from and facing the shell interior surface (36) over major area of the panel exterior surface. A gap (80) is formed between the heat shield exterior surface (34) and shell interior surface (36) along at least a major portion of the perimeter of the heat shield panel (28).

    Abstract translation: 燃烧器隔热板（28）相对于燃烧器壳体（22）固定，以便在面板外表面的主要区域上保持与壳体内表面（36）间隔开并面向壳体内表面（36）的面板外表面（34）。 沿着隔热板（28）的周边的至少大部分，在隔热罩外表面（34）和壳体内表面（36）之间形成间隙（80）。

    Gas turbine combustor
    20.
    发明公开
    Gas turbine combustor 有权
    燃烧室的燃气轮机

    公开(公告)号：EP1318353A3

    公开(公告)日：2004-04-14

    申请号：EP02258413.0

    申请日：2002-12-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Burd, Steven W. ,  Graves, Charles B. ,  Siskind, Kenneth S.

    IPC: F23R3/06 ,  F23R3/00 ,  F23R3/60 ,  F23M5/08 ,  F23M5/02

    CPC classification number: F23R3/60 ,  F23M5/02 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03044

    Abstract: A combustor 10 for a gas turbine engine is provided which includes a plurality of liner segments 12 and a support shell 14. The support shell 14 includes an interior 16 and an exterior 18 surface, a plurality of mounting holes 20, and a plurality of impingement coolant holes 22 extending through the support shell 14. Each liner segment 12 includes a panel 24 and a plurality of mounting studs 32. The panel 24 includes a face surface 34 and a back surface 36, and a plurality of normal or inclined coolant holes 38 extending therethrough. The back surface 36 of the panel 24 has a surface profile for improving the heat transfer properties of a liner segment without substantial increase in pressure drop across the combustor.

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