公开(公告)号：JPH11237048A

公开(公告)日：1999-08-31

申请号：JP35368098

申请日：1998-12-14

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: PROBLEM TO BE SOLVED: To suppress the formation of a nitrogen oxide and at the same time improve the durability of an injector and combustion equipment. SOLUTION: A fuel injector 10 for gas turbine engine includes a scroll 18 where an edge part forms an entrance slot 36, and the slot 36 guides primary combustion air, along a tangential direction, into a mixing room 28 that is bounded by edge plates 14 and 16 being separated from the scroll 18 in the longitudinal direction. A row of fuel injection channels 42 is extended over the length of the slot 36. The injector 10 also includes a center body 48 with a wide tip part 54 for discharging flame. The center body 48 prevents combustion flame from flowing into the mixing room 28 and improves the durability of the combustion equipment 10 by discharging flame when it flows in. Also, by controlling a fuel being discharged through the injection channel 42, the capacity for the center body 48 to discharge flame can be improved and at the same time the flame can be stabilized spatially.

公开(公告)号：JPH10196954A

公开(公告)日：1998-07-31

申请号：JP36523397

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

Abstract: PROBLEM TO BE SOLVED: To reduce an acoustic effect for guiding excess combustor pressure change in a gas turbine engine. SOLUTION: Fuel-air mixture is burnt in a combustor at a downstream of an outlet surface 124 of a fuel nozzle 10. Recirculating regions 200, 300 generated by the nozzle 10 in all operating states of the engine are disposed at an interval to the surface 124, and the combustion product is isolated from the fuel and air of a mixing region 28 of the nozzle 10.

公开(公告)号：JPH10196953A

公开(公告)日：1998-07-31

申请号：JP36523297

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A

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

Abstract: PROBLEM TO BE SOLVED: To increase an operating life when a tangential inlet fuel nozzle is used for a gas turbine engine. SOLUTION: A tangential inlet fuel nozzle 10 has a combustor inlet port 20 for allowing discharge of the air and fuel into a combustor. This port 20 has a convergent surface 116, a combustor surface 122 and a cylindrical surface 118 extended between these surfaces. The surface 116 is extended at a first distance 126 along a longitudinal axis 26 of the nozzle 10. The surface 118 is extended at a second distance 128 along the axis 26, and the distance 128 is at least 30% of the first distance 126.

公开(公告)号：JPH10196952A

公开(公告)日：1998-07-31

申请号：JP36523197

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  KRAMER STEPHEN K ,  SOWA WILLIAM A

IPC: F02C7/232 ,  F02M61/16 ,  F23C7/00 ,  F23C7/02 ,  F23C99/00 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34 ,  F23C11/00

Abstract: PROBLEM TO BE SOLVED: To displace a flame moved to a mixing region of a fuel nozzle by reducing a trend of stabilizing a burning flame in the nozzle. SOLUTION: Air inlet slots 36, 38 are formed between superposed ends of two offset cylindrical arc-like scroll members 22, 24 of a tangential air inlet fuel nozzle 10. An end plate 18 has a combustor inlet port 20, and the other end plate 16 seals a flowing region of the nozzle. The members 22, 24 are fixed between the end plates. A central body 12 is provided between the members coaxial with a longitudinal axis 26. The body has a base 58 and an inner passage 64. The base 58 has at least one air supply hole extended through the base. The body 12 has a truncated conical part 86 and an aerodynamic ramp, which prevent backflow and flame stability between the end plates.

公开(公告)号：JPH11350975A

公开(公告)日：1999-12-21

申请号：JP12968699

申请日：1999-05-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOWA WILLIAM A ,  KENDRICK DONALD W ,  CHIAPPETTA LOUIS M

IPC: F02C3/30 ,  F02C7/22 ,  F23C7/00 ,  F23D11/40 ,  F23D14/02 ,  F23D14/82

Abstract: PROBLEM TO BE SOLVED: To prevent an increase of exhaust gas emissions and also to prevent the deterioration of frame stability even when operated under deteriorated conditions, by making the fuel jet discharged from a passage hit an adjacent scroll so as not to reach the center body in the radial direction. SOLUTION: In a fuel injection system, the position of a passage 52 is indicated as an offset distance δ with respect to a slot discharge surface 46. In the passage 52, a discharge opening 54 is circumferentially upstream of the intake slot discharge surface 46. The offset distance δ is made such that an average trajectory 78b of a reflected fuel jet 76b lightly touches a rear peripheral edge 36 of an adjacent scroll 18, even when, at the very least, the injector is operated under deteriorated conditions. As a result of determining the position of the passage according to this type of standard, the fuel jet 76b hits the rear peripheral edge of the adjacent scroll 18. The adjacent scroll 18 functions as a physical barrier in restricting the intrusion of the fuel jet 76b in the radial direction.

公开(公告)号：JPH10196955A

公开(公告)日：1998-07-31

申请号：JP36523497

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A ,  KRAMER STEPHEN K

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

Abstract: PROBLEM TO BE SOLVED: To reduce the trend that a flame is stabilized in the tangential inlet nozzle of a gas turbine engine. SOLUTION: Fuel and the air are mixed in the mixing section 28 of a fuel nozzle 10 to produce a fuel/air mixture which is isolated from combustion products by sustaining the axial velocity through the mixing section 28 at a sufficiently high level and combining the face of an internal passage 64 of a central body 12 (supplied or not supplied with fuel) with the face of a burner inlet port 20.

公开(公告)号：DE69912517D1

公开(公告)日：2003-12-11

申请号：DE69912517

申请日：1999-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOWA WILLIAM A ,  KENDRICK DONALD W ,  CHIAPPETTA LOUIS M

IPC: F02C3/30 ,  F02C7/22 ,  F23C7/00 ,  F23D11/40 ,  F23D14/02 ,  F23D14/82 ,  F23D17/00

Abstract: A premixing fuel injector (10) is provided, comprising a centerbody (58) and at least two circumferentially neighboring scrolls (18). Each scroll (18) has a circumferentially leading end (28) and a circumferentially trailing end (34) that terminates at a trailing edge (36). The scrolls (18) collectively circumscribe the centerbody (58) to radially bound a mixing chamber (24). The leading end (28) of each scroll and the trailing end (34) of the neighboring scroll define radially inner and outer extremities of an intake slot (42) for admitting a stream of air into the mixing chamber. The leading end of at least one of the scrolls (18) includes an array of axially distributed fuel injection passages (52) for introducing fuel into the air stream. The injector (10) can be used in both a prescribed state of operation and a degraded state of operation.

公开(公告)号：CA2255549C

公开(公告)日：2007-04-10

申请号：CA2255549

申请日：1998-12-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MORFORD STEPHEN A ,  SOWA WILLIAM A ,  SNYDER TIMOTHY S ,  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 slo ts (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 fu el injection passages (42) extends along the length of the slots. The passage stray is configured to inject a primary fuel nonuniformly along the length of the air entry slots a nd 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 wi th the injector's discharge plane (22) and a secondary fuel conduit (80) extending through .th e 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 centerbod y improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber (28) and reliably disgorging any flame that is ingested. The controlled fuel penetration depth reinforces the flame disgorging capability of the centerbody by preventing fuel from penetrating into the slowly moving boundary layer attached to the centerbody (48). The bluff character of the centerbody, in combination with its longitudinal alignment with the fuel injector discharge plane, makes the centerbody capable of anchoring the flame at the discharge plane so that combustion occurs aft of the discharge plane where t he combustion flame is unlikely to damage the scrolls or centerbody. Introducti on of fuel or fuel and air through the openings in the bluff tip encourage the flame to become anchored to the tip and therefore spatially stabilizes the flame, resulting in additional attenuation of acoustic oscillations and further improved combustor durability. The longitudinally nonuniform injection of primary fuel compensates for any mixing nonuniformities attributable to the flame disgorging centerbody and therefore augments flame stability. The injector and an associated method of premixing fuel and air prior to combustion suppress formation of nitrous oxides, and improve the durability of both the injector and the combustor.

公开(公告)号：DE69733244T2

公开(公告)日：2005-08-25

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：CA2225319A1

公开(公告)日：1998-06-20

申请号：CA2225319

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  KRAMER STEPHEN K ,  SOWA WILLIAM A

IPC: F02C7/232 ,  F02M61/16 ,  F23C7/00 ,  F23C7/02 ,  F23C99/00 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34 ,  F23R3/14 ,  F23D14/02 ,  F23D14/48 ,  F23D14/62

Abstract: A tangential air entry fuel nozzle has a longitudinal axis and two cylindrical-a rc scrolls with the centerline of each offset from that of the other. Overlapping e nds of these scrolls form an air inlet slot therebetween for the introduction of an air/fuel mixture into the fuel nozzle. A combustor-end endplate has a central opening to permit air an d fuel to exit into a combustor, while at the opposite end another endplate blocks the noz zle flow area. The scrolls are secured between these endplates. A centerbody is located b etween the scrolls coaxial with the axis. The centerbody has a base which includes at l east one air supply port extending therethrough, and an internal passageway. The centerbody i ncludes a frustum portion and aerodynamic ramps that prevent flow reversal and flame stabilization between the endplates.