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    Combustor turbine interface
    22.
    发明公开
    Combustor turbine interface 有权
    燃烧室的涡轮过渡

    公开(公告)号：EP1801356A3

    公开(公告)日：2011-01-26

    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).

    Local cooling hole pattern
    24.
    发明公开
    Local cooling hole pattern 有权
    局部冷却孔图案

    公开(公告)号：EP1798474A3

    公开(公告)日：2010-06-30

    申请号：EP06256259.0

    申请日：2006-12-08

    Applicant: United Technologies Corporation

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

    IPC: F23R3/06

    CPC classification number: F23R3/06

    Abstract: A combustor assembly includes an inner and an outer liner defining a combustion chamber. The inner and outer liner includes a plurality of cooling holes that are spaced a specified distance apart. The cooling holes include a specified inclination angle (54) and circumferential angle (56). A first group (58) of cooling holes is spaced apart according to a uniform geometric pattern and density. A second group (62; 68; 72) disposed between the first group (58) and some structural feature (32; 38; 40) within the liner assembly is disposed at a non-uniform pattern and a hole density equal to the density of the first group of cooling holes. The non-uniform cooling hole arrangement increases cooling flow effectiveness to accommodate local disturbances and thermal properties.

    Hole pattern for gas turbine combustor
    25.
    发明公开
    Hole pattern for gas turbine combustor 审中-公开
    LochmusterfürGasturbinenbrennkammer

    公开(公告)号：EP2133628A2

    公开(公告)日：2009-12-16

    申请号：EP09250924.9

    申请日：2009-03-30

    Applicant: United Technologies Corporation

    Inventor： Shelley, Jonathan K. ,  Burd, Steven W. ,  Cheung, Albert K. ,  Kozola, Stuart L.

    IPC: F23R3/06

    CPC classification number: F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A combustor for a turbine engine includes an outer liner (34) having a row of circumferentially distributed outer combustion air holes and an inner liner (32) circumscribed by the outer liner (34) and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners (32, 34) each include at least a major air hole (104) having a first hole size, an intermediate air hole (108) having a second hole size, and a minor air hole (106) having a third hole size. The first, second, and third hole sizes are all different from each other.

    Abstract translation: 用于涡轮发动机的燃烧器包括具有一排周向分布的外部燃烧气孔的外衬套（34​​）和由外衬套（34​​）外接的内衬（32），并且具有一排周向分布的内燃气孔。 内衬层和外衬层（32,34）各自至少包括具有第一孔尺寸的主空气孔（104），具有第二孔尺寸的中间空气孔（108）和具有第二孔尺寸的小空气孔（106） 第三洞大小。 第一，第二和第三孔的尺寸都是不同的。

    Gas turbine combustor
    27.
    发明公开
    Gas turbine combustor 有权
    BrennkammerfürGasturbine

    公开(公告)号：EP1318353A2

    公开(公告)日：2003-06-11

    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

    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.

    Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器10，其包括多个衬垫段12和支撑壳14.支撑壳14包括内部16和外部18表面，多个安装孔20和多个冲击 每个衬垫段12包括一个面板24和多个安装螺柱32.面板24包括一个表面34和一个后表面36以及多个正常或倾斜的冷却剂孔38 延伸穿过。 面板24的后表面36具有用于改善衬套段的传热性能而不会显着增加穿过燃烧器的压降的表面轮廓。

    Gas turbine combustor
    30.
    发明公开
    Gas turbine combustor 审中-公开

    公开(公告)号：EP1775516A3

    公开(公告)日：2010-06-30

    申请号：EP06255344.1

    申请日：2006-10-17

    Applicant: United Technologies Corporation

    Inventor： Burd, Steven W. ,  Sowa, William ,  Cheung, Albert K. ,  Kramer, Stephen K. ,  Hokes, James ,  Smith, Reid Dyer Curtis

    IPC: F23R3/50

    CPC classification number: F23R3/50

    Abstract: A combustor assembly (12) includes a convergent segment (34) followed by a divergent segment (36) to advantageously improve combustion. The combustor assembly includes a first segment (34) beginning at a forward end (24) that transitions to a second segment (36) past a transition segment (58) in a direction along a combustor axis (22) toward an aft end (26). The reduction in cross-sectional area within the first segment (34) provides desirable fuel and air mixing properties. The convergent first segment (34) in combination with the divergent second segment (36) decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

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