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    COMBUSTION CAN FOR TURBINE ENGINE
    1.
    发明专利
    COMBUSTION CAN FOR TURBINE ENGINE 失效

    公开(公告)号：JP2000304261A

    公开(公告)日：2000-11-02

    申请号：JP2000115027

    申请日：2000-04-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOKE JAMES B ,  MOUNTZ DARYL B ,  OLSEN HOWARD ,  SONNTAG ROBERT M

    IPC: F23R3/42 ,  F23D11/00 ,  F23R3/06 ,  F23R3/28 ,  F23R3/46

    Abstract: PROBLEM TO BE SOLVED: To reduce exhausting of an NOx, a UHC and smoke by incorporating a first row passing a combustor liner at an intermediate portion of the liner, a second row coincident with the first row rear in a circumferential direction and a third row rear from the first row in a row of a dilution hole, and incorporating a specific size and a circumferential array in the hole of the third row. SOLUTION: In order to supply a jet of dilute air in a combustion area 50, a first row 52 of a dilute hole passes a liner at a substantially intermediately axially common position of an effective axial length L of the liner. A second row 54 of the hole passes the liner at a rear common axial position from the row 52 at a predetermined distance. A third row 56 of the hole passes the liner a rear common axial position at the specific distance. The specific length is longer than a predetermined distance. An arrangement with the size and circumferential direction of the hole 56 of the third row is selected to simulate to a profile specified in a flow of combustion gas generated from a rear end of the combustion can 18.

    4.
    发明专利
    未知

    公开(公告)号：AT330183T

    公开(公告)日：2006-07-15

    申请号：AT00303179

    申请日：2000-04-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOKE JAMES B ,  MOUNTZ DARYL B ,  OLSEN HOWARD ,  SONNTAG ROBERT M

    IPC: F23R3/42 ,  F23D11/00 ,  F23R3/06 ,  F23R3/28 ,  F23R3/46

    Abstract: A low emissions combustor can 18 for an aircraft gas turbine engine includes a louvered combustor liner 24 with three arrays 52 of dilution holes 52, 54, 56. The first hole array comprises twelve equally sized, equiangularly distributed holes that penetrates the liner about midway along its axial length. The second hole array 54 comprises twelve equally sized holes, smaller than the holes of the first array, that penetrate the liner a predetermined distance aft of the first hole array 52. The holes of the second array 54 are equiangularly distributed and each second hole is circumferentially aligned with a first hole. A third hole array 56 penetrates the liner a predefined distance aft of the first array. The third holes are nonuniformly sized and nonequiangularly distributed to regulate the spatial temperature profile of combustion gases exiting the combustor can. The quantity, size, distribution and location of the holes mitigates undesirable exhaust emissions without affecting the performance or durability of the engine. Accordingly, the combustor can may be used to replace an existing combustor can in an older generation gas turbine engine.

    Carcasa de escape de turbina de alta durabilidad
    5.
    发明专利
    Carcasa de escape de turbina de alta durabilidad 未知

    公开(公告)号：ES2781574T3

    公开(公告)日：2020-09-03

    申请号：ES13804715

    申请日：2013-06-14

    Applicant: UNITED TECHNOLOGIES CORP ,  GKN AEROSPACE SWEDEN AB

    Inventor： MOUNTZ DARYL B ,  KAPUSTKA THEODORE W ,  LEVASSEUR GLENN ,  BORG MARCUS ,  BERGLUND JOAKIM ,  SVAHN ANDERS ,  OCKBORN JOHAN ,  PETTERSSON BENGT

    IPC: F01D25/16 ,  F01D25/00

    Abstract: Una carcasa de escape de turbina (100) que comprende: un alojamiento externo configurado para ser asegurado dentro de un motor de turbina de gas; un cubo central (102); y puntales (116) que incluyen perfiles aerodinámicos y que se extienden entre el alojamiento externo y el cubo central (102), los puntales (116) que están formados al menos en parte de un primer material, y el cubo central (102) formado al menos en parte de un segundo material, en donde el primer material se selecciona para tener una mejor resistencia a altas temperaturas y para mantener propiedades metalúrgicas a altas temperaturas que el segundo material; caracterizada por que el cubo central (102) tiene una pluralidad de muñones (110) que se extienden radialmente hacia fuera y los puntales (116) están soldados a los muñones (110) de manera que las partes radialmente internas de los perfiles aerodinámicos estén formadas por los muñones (110) del segundo material, y las partes radialmente hacia fuera estén formadas por los puntales (116) y el primer material.

    6.
    发明专利
    未知

    公开(公告)号：DE60028648D1

    公开(公告)日：2006-07-27

    申请号：DE60028648

    申请日：2000-04-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOKE JAMES B ,  MOUNTZ DARYL B ,  OLSEN HOWARD ,  SONNTAG ROBERT M

    IPC: F23R3/06 ,  F23R3/42 ,  F23D11/00 ,  F23R3/28 ,  F23R3/46

    Abstract: A low emissions combustor can 18 for an aircraft gas turbine engine includes a louvered combustor liner 24 with three arrays 52 of dilution holes 52, 54, 56. The first hole array comprises twelve equally sized, equiangularly distributed holes that penetrates the liner about midway along its axial length. The second hole array 54 comprises twelve equally sized holes, smaller than the holes of the first array, that penetrate the liner a predetermined distance aft of the first hole array 52. The holes of the second array 54 are equiangularly distributed and each second hole is circumferentially aligned with a first hole. A third hole array 56 penetrates the liner a predefined distance aft of the first array. The third holes are nonuniformly sized and nonequiangularly distributed to regulate the spatial temperature profile of combustion gases exiting the combustor can. The quantity, size, distribution and location of the holes mitigates undesirable exhaust emissions without affecting the performance or durability of the engine. Accordingly, the combustor can may be used to replace an existing combustor can in an older generation gas turbine engine.

    9.
    发明专利
    未知

    公开(公告)号：DE60028648T2

    公开(公告)日：2007-01-18

    申请号：DE60028648

    申请日：2000-04-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOKE JAMES B ,  MOUNTZ DARYL B ,  OLSEN HOWARD ,  SONNTAG ROBERT M

    IPC: F23R3/06 ,  F23R3/42 ,  F23D11/00 ,  F23R3/28 ,  F23R3/46

    Abstract: A low emissions combustor can 18 for an aircraft gas turbine engine includes a louvered combustor liner 24 with three arrays 52 of dilution holes 52, 54, 56. The first hole array comprises twelve equally sized, equiangularly distributed holes that penetrates the liner about midway along its axial length. The second hole array 54 comprises twelve equally sized holes, smaller than the holes of the first array, that penetrate the liner a predetermined distance aft of the first hole array 52. The holes of the second array 54 are equiangularly distributed and each second hole is circumferentially aligned with a first hole. A third hole array 56 penetrates the liner a predefined distance aft of the first array. The third holes are nonuniformly sized and nonequiangularly distributed to regulate the spatial temperature profile of combustion gases exiting the combustor can. The quantity, size, distribution and location of the holes mitigates undesirable exhaust emissions without affecting the performance or durability of the engine. Accordingly, the combustor can may be used to replace an existing combustor can in an older generation gas turbine engine.

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