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    COMBUSTION MACHINE FOR GAS TURBINE ENGINE
    1.
    发明专利
    COMBUSTION MACHINE FOR GAS TURBINE ENGINE 失效

    公开(公告)号：JPH1061954A

    公开(公告)日：1998-03-06

    申请号：JP17138297

    申请日：1997-06-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCKINNEY RANDAL G ,  DAVIS FRANKLIN J

    IPC: F02C7/18 ,  F23R3/10 ,  F23R3/26 ,  F23R3/28

    Abstract: PROBLEM TO BE SOLVED: To provide a fuel nozzle guide which can improve a cooling flow on a bulkhead heat shield without increasing the level of the cooling flow of a combustion machine in a gas turbine engine. SOLUTION: A nozzle guide 50 comprises a circular bushing 52 having a dimension enough to insert a nozzle 46 and one end part of the circular bushing 52 is linked to a nozzle guide retainer 56 while the other end part thereof forms a flange part 54 extending radially. The flange part 54 has a periphery part as peripheral portion away from a body part as body close to a link part of the circular bushing 52. The periphery part is extended in substance parallel with a combustion chamber bulkhead heat shield 58 while a rib is formed extending radially on the perimeter of the periphery part of the flange part 54. Each rib has a head end part and a tail end part and the tail end part is shaped into a circular arc. The vortex of a filmy cooling air passing between the end parts is reduced to supplement the bulkhead heat shield 58.

    AXIAL STAGED COMBUSTOR WITH RESTRICTED MAIN FUEL INJECTOR
    2.
    发明申请
    AXIAL STAGED COMBUSTOR WITH RESTRICTED MAIN FUEL INJECTOR 审中-公开
    带有限制的主燃料喷射器的轴式燃烧器

    公开(公告)号：WO2015147951A3

    公开(公告)日：2015-11-19

    申请号：PCT/US2015010082

    申请日：2015-01-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DAI ZHONGTAO ,  HOLLEY ADAM TAKASHI ,  MCKINNEY RANDAL G

    IPC: F23R3/28 ,  F02C7/22 ,  F23R3/30

    CPC classification number: F23R3/346 ,  F02C3/04 ,  F05D2220/32 ,  F23D14/70 ,  F23R3/12 ,  F23R3/286 ,  F23R3/343

    Abstract: A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that restricts flow at least at an interior portion of the flow path. A gas turbine engine is also disclosed.

    Abstract translation: 用于燃气涡轮发动机的燃烧器包括燃烧室，其具有在一端的先导喷射器和与引燃喷射器径向间隔开的至少一个主喷射器。 主喷射器包括具有塞子的流体流动路径，其至少在流动路径的内部部分限制流动。 还公开了一种燃气涡轮发动机。

    STEPPED HEAT SHIELD FOR A TURBINE ENGINE COMBUSTOR
    7.
    发明公开
    STEPPED HEAT SHIELD FOR A TURBINE ENGINE COMBUSTOR 审中-公开
    GESTUFTER HITZESCHILDFÜREINE TURBINENMOTORBRENNKAMMER

    公开(公告)号：EP3102884A4

    公开(公告)日：2017-03-01

    申请号：EP15743262

    申请日：2015-02-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MCKINNEY RANDAL G ,  CUNHA FRANK J ,  KOSTKA JR STANISLAV

    IPC: F23M5/00 ,  F02C3/14 ,  F02C7/24 ,  F23M5/08 ,  F23R3/42

    CPC classification number: F23R3/002 ,  F02C7/24 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/201 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.

    Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括具有外壳和隔热罩的燃烧器壁。 燃烧器壁限定穿过其中的骤冷孔。 燃烧器壁还在外壳和隔热罩之间限定一个空腔。 壳体限定空气被引导到空腔中的第一孔。 隔热罩包括至少部分地限定第二孔的导轨，该第二孔构造成将腔内的至少一些空气引导出燃烧器壁并且朝向骤冷孔。

    COMBUSTOR WITH AXIAL STAGING FOR A GAS TURBINE ENGINE
    8.
    发明公开
    COMBUSTOR WITH AXIAL STAGING FOR A GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机用带轴电路的燃烧室

    公开(公告)号：EP3008391A4

    公开(公告)日：2016-07-06

    申请号：EP14811456

    申请日：2014-06-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOKE JAMES B ,  MCKINNEY RANDAL G ,  CHEUNG ALBERT K

    IPC: F23R3/42 ,  F23R3/46

    CPC classification number: F23R3/346 ,  F23R3/002 ,  F23R3/06 ,  F23R3/14 ,  F23R3/42 ,  F23R3/50 ,  Y02T50/675

    Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.

    Abstract translation: 燃烧器是燃气涡轮发动机，其包括与燃烧室连通的轴向燃料喷射系统，所述轴向燃料喷射系统可操作以提供约10％-35％的燃烧气流。 径向燃料喷射系统与轴向燃料喷射系统下游的燃烧室连通，其中径向燃料喷射系统可操作以供应燃烧气流的约30％-60％。 多个稀释孔与所述径向燃料喷射系统下游的燃烧室连通，其中多个稀释孔可操作以供应约5％-20％的燃烧气流。

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