公开(公告)号：DE69832427T2

公开(公告)日：2006-07-27

申请号：DE69832427

申请日：1998-12-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SYNDER TIMOTHY S ,  MORFORD STEPHEN A ,  SOWA WILLIAM A ,  VAN DYKE KEVIN J

IPC: F23R3/28 ,  F23R3/30 ,  F23C7/00 ,  F23D14/74 ,  F23D14/82 ,  F23D17/00 ,  F23R3/12 ,  F23R3/34

Abstract: A tangential entry premixing fuel injector (10) for a gas turbine engine combustor includes a pair of offset scrolls (18) whose ends define a pair of entry slots (36) for admitting primary combustion air tangentially into a mixing chamber (28) bounded by the scrolls (18) and by longitudinally spaced endplates (14,16). An array of fuel injection passages (42) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height H. The injector also includes a flame disgorging centerbody (48) having a bluff tip (54) longitudinally aligned with the injector's discharge plane (22) and a secondary fuel conduit (80) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings (84) in the tip (54). The flame disgorging centerbody improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber (28) and reliably disgorging any flame that is ingested.

公开(公告)号：DE69733244D1

公开(公告)日：2005-06-16

申请号：DE69733244

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A

IPC: F02C9/28 ,  F02M61/16 ,  F02C7/232 ,  F23C7/00 ,  F23C7/02 ,  F23C9/00 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34

Abstract: A method of reducing pressure fluctuations in the combustor of a gas turbine engine resulting from the combustion of fuel and air therein comprises combusting a fuel/air mixture in a combustor downstream of the exit plane of a fuel nozzle assembly such that such recirculation zones generated by the fuel nozzle assembly are in spaced relation to the exit plane at all operating conditions of the engine.

公开(公告)号：DE69822102D1

公开(公告)日：2004-04-08

申请号：DE69822102

申请日：1998-12-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A ,  MORFORD STEPHEN A ,  VAN DYKE KEVIN J

IPC: F23R3/30 ,  F23C7/00 ,  F23D14/74 ,  F23D14/82 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/34

Abstract: A tangential entry premixing fuel injector (10) for a gas turbine engine combustor includes a pair of offset scrolls (18) whose ends define a pair of entry slots (36) for admitting primary combustion air tangentially into a mixing chamber (28) bounded by the scrolls (18) and by longitudinally spaced endplates (14,16). An array of fuel injection passages (42) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height H. The injector also includes a flame disgorging centerbody (48) having a bluff tip (54) longitudinally aligned with the injector's discharge plane (22) and a secondary fuel conduit (80) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings (84) in the tip (54). The flame disgorging centerbody improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber (28) and reliably disgorging any flame that is ingested.

公开(公告)号：RU2195575C2

公开(公告)日：2002-12-27

申请号：RU97121008

申请日：1997-12-19

Applicant: TATA DELAWARE ,  UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A

IPC: F02C9/28 ,  F02M61/16 ,  F02C7/232 ,  F23C7/00 ,  F23C7/02 ,  F23C9/00 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34

公开(公告)号：CA2475380A1

公开(公告)日：1999-06-15

申请号：CA2475380

申请日：1998-12-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOWA WILLIAM A ,  VAN DYKE KEVIN J ,  MORFORD STEPHEN A

IPC: F23R3/28

公开(公告)号：CA2225393A1

公开(公告)日：1998-06-20

申请号：CA2225393

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOWA WILLIAM A ,  SNYDER TIMOTHY S

IPC: F02C7/232 ,  F02C7/22 ,  F02M61/16 ,  F23C7/00 ,  F23C7/02 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/14 ,  F23D14/02 ,  F23D14/62

Abstract: A tangential air entry fuel nozzle has a combustor inlet port to permit air and fuel to exit into a combustor. The port includes a convergent surface, a combustor su rface, and a cylindrical surface extending therebetween. The convergent surface extends a f irst distance along the longitudinal axis of the nozzle, the cylindrical surface exte nds a second distance along the axis, and the second distance is at least 30% of the first di stance.

公开(公告)号：CA2225376A1

公开(公告)日：1998-06-20

申请号：CA2225376

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A

IPC: F02C7/232 ,  F02C9/28 ,  F02M61/16 ,  F23C7/00 ,  F23C7/02 ,  F23C9/00 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34 ,  F23R3/14 ,  F23D14/02 ,  F23D14/62

Abstract: A method of reducing pressure fluctuations in the combustor of a gas turbine engine resulting from the combustion of fuel and air therein comprises combustin g a fuel/air mixture in a combustor downstream of the exit plane of a fuel nozzle as sembly such that such recirculation zones generated by the fuel nozzle assembly are in spaced relation to the exit plane and the combustion products are isolated from the fue l and air in the mixing zone at all operating conditions of the engine.