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    FLOAT WALL COMBUSTOR PANELS HAVING AIRFLOW DISTRIBUTION FEATURES
    12.
    发明申请
    FLOAT WALL COMBUSTOR PANELS HAVING AIRFLOW DISTRIBUTION FEATURES 审中-公开

    公开(公告)号：US20190128187A1

    公开(公告)日：2019-05-02

    申请号：US15795301

    申请日：2017-10-27

    Applicant: United Technologies Corporation

    Inventor： Jason Shenny ,  John J. Rup, JR. ,  Robert M. Sonntag ,  James B. Hoke ,  San Quach ,  Richard G. Ullrich

    IPC: F02C7/18 ,  F23R3/00 ,  F23R3/04

    Abstract: Combustor panels including panel bodies with first and second sides, a pin array extending from the first side, wherein each pin extends a first height, has a pin diameter, and is separated from adjacent pins by a pin array separation distance. A structural protrusion extends from the first side. No pins of the pin array are located within a flashing distance that is equal to a protrusion separation distance plus half of the pin diameter, wherein a location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. At least one pin array extension is integrally formed with the structural protrusion, the pin array extension extending along the first side to a position that replaces a pin of the pin array that would be within the flashing distance.

    COMBUSTOR PANEL COOLING ARRANGEMENTS
    13.
    发明申请
    COMBUSTOR PANEL COOLING ARRANGEMENTS 审中-公开

    公开(公告)号：US20180298819A1

    公开(公告)日：2018-10-18

    申请号：US15490189

    申请日：2017-04-18

    Applicant: United Technologies Corporation

    Inventor： Dennis M. Moura ,  James B. Hoke ,  Reza Rezvani

    IPC: F02C7/12 ,  F23R3/00

    Abstract: Combustor panels for use in gas turbine engine combustors having a panel body having a peripheral rail around a periphery of the panel body, a first boss formed on the panel body and surrounding a first aperture that passes through the panel body, and a first webbing that extends from the peripheral rail toward the first boss. A first annular channel is formed between the first webbing and the first boss and surrounds the first boss and a first web pocket is formed within the first webbing between the peripheral rail and the first boss and defines a local extension of the first annular channel extending from the first boss to the peripheral rail.

    COMBUSTOR WITH AXIAL STAGING FOR A GAS TURBINE ENGINE
    17.
    发明申请
    COMBUSTOR WITH AXIAL STAGING FOR A GAS TURBINE ENGINE 审中-公开
    燃气轮机用于燃气涡轮发动机

    公开(公告)号：US20160123596A1

    公开(公告)日：2016-05-05

    申请号：US14895784

    申请日：2014-06-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James B. Hoke ,  Randal G. McKinney ,  Albert K. Cheung

    IPC: F23R3/34 ,  F23R3/06 ,  F23R3/42 ,  F23R3/00

    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。

    Combustor with axial staging for a gas turbine engine
    19.
    发明授权
    Combustor with axial staging for a gas turbine engine 有权

    公开(公告)号：US11143407B2

    公开(公告)日：2021-10-12

    申请号：US14895784

    申请日：2014-06-11

    Applicant: United Technologies Corporation

    Inventor： James B. Hoke ,  Randal G. McKinney ,  Albert K. Cheung

    IPC: F23R3/34 ,  F23R3/06 ,  F23R3/14 ,  F23R3/50 ,  F23R3/00 ,  F23R3/42

    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.

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