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.

公开(公告)号：AT452223T

公开(公告)日：2010-01-15

申请号：AT05255381

申请日：2005-09-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BURD STEVEN W ,  SCHLICHTING KEVIN W ,  SONNTAG ROBERT M

IPC: C23C30/00 ,  F01D25/00

Abstract: An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

公开(公告)号：DE602005018303D1

公开(公告)日：2010-01-28

申请号：DE602005018303

申请日：2005-09-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BURD STEVEN W ,  SCHLICHTING KEVIN W ,  SONNTAG ROBERT M

IPC: C23C30/00 ,  F01D25/00

Abstract: An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

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.

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.

公开(公告)号：SG121970A1

公开(公告)日：2006-05-26

申请号：SG200506536

申请日：2005-10-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BURD STEVEN W ,  SONNTAG ROBERT M ,  SCHLICTHING KEVIN W

Abstract: An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

公开(公告)号：GB2518750A

公开(公告)日：2015-04-01

申请号：GB201415057

申请日：2013-01-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： EASTWOOD JONATHAN JEFFERY ,  WONG JOEY ,  SONNTAG ROBERT M

IPC: F23R3/00 ,  F23R3/50 ,  F23R3/60

Abstract: An annular combustor includes an annular outer shell that includes a first flange that defines an inner diameter IDOS and an annular inner shell that includes a second flange that defines an outer diameter ODIS. An annular hood includes a radially outer hood flange and a radially inner hood flange. A bulkhead includes a radially outer bulkhead flange that defines an outer diameter ODB and a radially inner bulkhead flange that defines an inner diameter IDB. The first flange is secured at a radially outer joint between the radially outer hood flange and the radially outer bulkhead flange. The second flange is secured at a radially inner joint between the radially inner hood flange and the radially inner bulkhead flange. The IDOS and the ODB define a ratio R1 of IDOS/ODB that is 0.998622-1.001129, and the IDB and the ODIS define a ratio R2 of IDB/ODIS that is 0.998812-1.001388.

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.

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。

公开(公告)号：EP2877726A4

公开(公告)日：2016-08-03

申请号：EP13822793

申请日：2013-07-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BANGERTER JAMES P ,  DUHAMEL DENNIS J ,  SONNTAG ROBERT M ,  REZVANI REZA

IPC: F02C3/14 ,  F01D9/02 ,  F02C7/00 ,  F02C7/20 ,  F23R3/00 ,  F23R3/06 ,  F23R3/50

CPC classification number: F01D9/023 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/00012 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: A turbine engine assembly includes a combustor and a stator vane arrangement having a plurality of stator vanes. The combustor includes a combustor wall that extends axially from a combustor bulkhead to a distal combustor wall end, which is located adjacent to the stator vane arrangement. The combustor wall includes a support shell with a plurality of impingement apertures, and a heat shield with a plurality of effusion apertures. The combustor wall end includes a plurality of circumferentially extending film cooled regions. At least one of the film cooled regions is circumferentially aligned with one of the stator vanes and includes a cooling aperture.

Abstract translation: 涡轮发动机组件包括具有多个定子叶片的燃烧器和定子叶片装置。 燃烧器包括从燃烧器隔板轴向延伸到位于邻近定子叶片装置的远侧燃烧器壁端部的燃烧室壁。 燃烧器壁包括具有多个冲击孔的支撑壳和具有多个喷射孔的隔热罩。 燃烧器壁端部包括多个周向延伸的膜冷却区域。 薄膜冷却区域中的至少一个与定子叶片中的一个周向对齐并且包括冷却孔。