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    COMBUSTOR FOR GAS TURBINE ENGINE
    1.
    发明专利
    COMBUSTOR FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：JP2003185139A

    公开(公告)日：2003-07-03

    申请号：JP2002354301

    申请日：2002-12-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BURD STEVEN W ,  SISKIND KENNETH S ,  GRAVES CHARLES B

    IPC: F23R3/42 ,  F23M5/02 ,  F23R3/00 ,  F23R3/06 ,  F23R3/60

    Abstract: PROBLEM TO BE SOLVED: To provide a combustor capable of improving a heat transfer, hardly increasing a pressure drop. SOLUTION: This combustor for gas turbine engine comprises a plurality of liner segments 12 and a support shell. The support shell comprises an inner surface, an outer surface, a plurality of mounting holes, and a plurality of impingement cooling holes extendedly passed through the support shell. Each of the liner segments 12 comprises a panel 24 and a plurality of mounting studs 32. The panel 24 comprises a front surface, a rear surface 36, and a plurality of cooling holes 38 extendedly passed through these surfaces. The rear surface 36 of the panel 24 comprises a surface profile for preventing the drop of a pressure passing in the combustor from substantially increasing and increasing the heat transfer of the liner segments 12. COPYRIGHT: (C)2003,JPO

    LOW NOX COMBUSTOR FOR GAS TURBINE ENGINE
    2.
    发明专利
    LOW NOX COMBUSTOR FOR GAS TURBINE ENGINE 失效

    公开(公告)号：JPH11257665A

    公开(公告)日：1999-09-21

    申请号：JP37287298

    申请日：1998-12-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOKE JAMES B ,  SEGALMAN IRVING ,  SISKIND KENNETH S ,  SMITH REID D C ,  STURGESS GEOFFREY J

    IPC: F23R3/26 ,  F23C6/04 ,  F23C7/00 ,  F23C7/02 ,  F23D11/10 ,  F23R3/06 ,  F23R3/58

    Abstract: PROBLEM TO BE SOLVED: To contribute to the reduction of discharging of NOx in a gas turbine engine by a method wherein the air stream of a specified amount is introduced from the air port of a combustor at the downstream of a dome by a specified distance into a fuel air spray pattern. SOLUTION: A combustion chamber 6 is provided with side walls 7, 8, connected to a dome or an end surface 9, so as to form a slender and annular combustion chamber 11. Fuel and a first specified amount of air stream are injected into the combustion chamber 6 to form uniformly distributed fuel air spray pattern, flowing at the downstream of the combustion chamber 6 and mixed so as to contain highly rich fuel. A second specified amount of air stream is introduced from the dome 9 into the fuel air spray pattern through the air port 17 of a combustor at the downstream of the dome 9 by a first specified distance. In this case, the first specified distance is 0.75 times of the height of the dome 9 and the second specified amount of air stream is the amount of dilute air enough to cause rapid mixing and quenching of mixture of fuel and air in the mixture of dilute fuel and air.

    4.
    发明专利
    未知

    公开(公告)号：DE60227769D1

    公开(公告)日：2008-09-04

    申请号：DE60227769

    申请日：2002-12-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BURD STEVEN W ,  GRAVES CHARLES B ,  SISKIND KENNETH S

    IPC: F23R3/06 ,  F23R3/42 ,  F23M5/02 ,  F23M5/08 ,  F23R3/00 ,  F23R3/60

    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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