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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
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.
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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
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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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
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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Patent Agency Ranking
公开(公告)号：GB2169356B
公开(公告)日：1988-08-17
申请号：GB8529792
申请日：1985-12-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： OLSEN HOWARD
Abstract: A coolable stator assembly formed of wall segments 36 for bounding a working medium flow path 14 is disclosed. The wall segments extend circumferentially about the working medium flow path and are circumferentially spaced leaving a clearance gap G therebetween. A duct 148 for cooling air is formed by the facing sides 144, 146 of the wall segments and a pair of radially spaced seal elements such as an inner seal plate 134 and an outer air seal plate 136. In one embodiment, a primary flow path for cooling air extends radially outwardly of the wall segments and the working medium flow path extends radially inwardly of the wall segments. The duct is pressurized with cooling air from an adjacent location at an intermediate pressure between the primary flow path 32 and the working medium flow path 14.
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公开(公告)号：DE3544117A1
公开(公告)日：1986-06-26
申请号：DE3544117
申请日：1985-12-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： OLSEN HOWARD
Abstract: A coolable stator assembly formed of wall segments 36 for bounding a working medium flow path 14 is disclosed. The wall segments extend circumferentially about the working medium flow path and are circumferentially spaced leaving a clearance gap G therebetween. A duct 148 for cooling air is formed by the facing sides 144, 146 of the wall segments and a pair of radially spaced seal elements such as an inner seal plate 134 and an outer air seal plate 136. In one embodiment, a primary flow path for cooling air extends radially outwardly of the wall segments and the working medium flow path extends radially inwardly of the wall segments. The duct is pressurized with cooling air from an adjacent location at an intermediate pressure between the primary flow path 32 and the working medium flow path 14.
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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
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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公开(公告)号：FR2574857A1
公开(公告)日：1986-06-20
申请号：FR8518683
申请日：1985-12-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： OLSEN HOWARD
Abstract: A coolable stator assembly formed of wall segments 36 for bounding a working medium flow path 14 is disclosed. The wall segments extend circumferentially about the working medium flow path and are circumferentially spaced leaving a clearance gap G therebetween. A duct 148 for cooling air is formed by the facing sides 144, 146 of the wall segments and a pair of radially spaced seal elements such as an inner seal plate 134 and an outer air seal plate 136. In one embodiment, a primary flow path for cooling air extends radially outwardly of the wall segments and the working medium flow path extends radially inwardly of the wall segments. The duct is pressurized with cooling air from an adjacent location at an intermediate pressure between the primary flow path 32 and the working medium flow path 14.
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公开(公告)号：GB2169356A
公开(公告)日：1986-07-09
申请号：GB8529792
申请日：1985-12-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： OLSEN HOWARD
Abstract: A coolable stator assembly formed of wall segments 36 for bounding a working medium flow path 14 is disclosed. The wall segments extend circumferentially about the working medium flow path and are circumferentially spaced leaving a clearance gap G therebetween. A duct 148 for cooling air is formed by the facing sides 144, 146 of the wall segments and a pair of radially spaced seal elements such as an inner seal plate 134 and an outer air seal plate 136. In one embodiment, a primary flow path for cooling air extends radially outwardly of the wall segments and the working medium flow path extends radially inwardly of the wall segments. The duct is pressurized with cooling air from an adjacent location at an intermediate pressure between the primary flow path 32 and the working medium flow path 14.
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