中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

4 records (took 0.027 seconds)

    COMBUSTOR WITH AXIAL STAGING FOR A GAS TURBINE ENGINE
    1.
    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。

    TURBINE ENGINE COMBUSTOR WALL WITH NON-UNIFORM DISTRIBUTION OF EFFUSION APERTURES
    2.
    发明公开
    TURBINE ENGINE COMBUSTOR WALL WITH NON-UNIFORM DISTRIBUTION OF EFFUSION APERTURES 审中-公开
    TURBINENMOTORBRENNKAMMERWAND MITUNGLEICHMÄSSIGERVERTEILUNG VONEFFUSIONSÖFFNUNGEN

    公开(公告)号：EP2864707A4

    公开(公告)日：2016-01-20

    申请号：EP13807403

    申请日：2013-06-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ERBAS-SEN NURHAK ,  HOKE JAMES B ,  CHEUNG ALBERT K ,  SONNTAG ROBERT M ,  SNYDER TIMOTHY S

    IPC: F23R3/42 ,  F02C3/14 ,  F02C7/00

    CPC classification number: F23R3/06 ,  F05B2260/201 ,  F05B2260/202 ,  F23R3/002 ,  F23R3/04 ,  F23R3/10 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03044

    Abstract: A turbine engine combustor wall includes support shell and a heat shield. The support shell includes shell quench apertures, first impingement apertures, and second impingement apertures. The combustor heat shield includes shield quench apertures fluidly coupled with the shell quench apertures, first effusion apertures fluidly coupled with the first impingement apertures, and second effusion apertures fluidly coupled with the second impingement apertures. The shield quench apertures and the first effusion apertures are configured in a first axial region of the heat shield, and the second effusion apertures are configured in a second axial region of the heat shield located axially between the first axial region and a downstream end of the heat shield. A density of the first effusion apertures in the first axial region is greater than a density of the second effusion apertures in the second axial region.

    Abstract translation: 涡轮发动机燃烧器壁包括支撑壳和隔热罩。 支撑壳包括壳体淬火孔，第一冲击孔和第二冲击孔。 燃烧器热屏蔽包括与壳体淬火孔流体连接的屏蔽骤冷孔，与第一冲击孔流体连接的第一渗出孔以及与第二冲击孔流体连接的第二渗出孔。 所述屏蔽骤冷孔和所述第一渗出孔被构造在所述隔热罩的第一轴向区域中，并且所述第二渗出孔构造在所述隔热罩的第二轴向区域中，所述第二轴向区域轴向位于所述第一轴向区域和所述第一轴向区域的下游端之间 隔热板。 第一轴向区域中的第一渗出孔的密度大于第二轴向区域中的第二渗出孔的密度。

Patent Agency Ranking