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公开(公告)号：CA2462753A1
公开(公告)日：2004-11-13
申请号：CA2462753
申请日：2004-04-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SNYDER TIMOTHY S , BRDAR CHRISTOPHER R , BUEY JOHN R
Abstract: A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway betwe en the inlet and outlet is at least partially bounded by outlet end surface portions divergin g from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.
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公开(公告)号：CA2190217C
公开(公告)日：2004-10-26
申请号：CA2190217
申请日：1996-11-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SNYDER TIMOTHY S , ROSFJORD THOMAS J
Abstract: A method of minimizing nitrous oxide emissions in a gas turbine engine includes a step of monitoring pressure fluctuations within a gas turbine engine combustor and a step of adjusting fuel flow to the combustor if the pressure fluctuations therein exceed a preestablished threshold. The combustor can be operated at the lowest levels of nitrous oxide emissions since the onset of a combustor instability and/or blowout is identified early to allow for corrective action so that such undesirable events are prevented.
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公开(公告)号：DE69727899T2
公开(公告)日：2004-07-29
申请号：DE69727899
申请日：1997-12-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SNYDER TIMOTHY S , SOWA WILLIAM A , KRAMER STEPHEN K
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公开(公告)号：DE69822102T2
公开(公告)日：2004-07-22
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
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.
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公开(公告)号：DE69727899D1
公开(公告)日：2004-04-08
申请号：DE69727899
申请日：1997-12-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SNYDER TIMOTHY S , SOWA WILLIAM A , KRAMER STEPHEN K
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Patent Agency Ranking
公开(公告)号：DE69619344T2
公开(公告)日：2002-11-28
申请号：DE69619344
申请日：1996-11-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SNYDER TIMOTHY S , ROSFJORD THOMAS J
Abstract: Pressure fluctuations within a gas turbine engine combustor are monitored and the fuel flow to the combustor adjusted if the pressure fluctuations exceed a preestablished threshold. The combustor can be operated at the lowest levels of nitrous oxide emissions since the onset of a combustor instability and/or blowout may be identified early by this method to allow for corrective action so that such undesirable events are prevented.
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公开(公告)号：DE69619344D1
公开(公告)日：2002-03-28
申请号：DE69619344
申请日：1996-11-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SNYDER TIMOTHY S , ROSFJORD THOMAS J
Abstract: Pressure fluctuations within a gas turbine engine combustor are monitored and the fuel flow to the combustor adjusted if the pressure fluctuations exceed a preestablished threshold. The combustor can be operated at the lowest levels of nitrous oxide emissions since the onset of a combustor instability and/or blowout may be identified early by this method to allow for corrective action so that such undesirable events are prevented.
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公开(公告)号：GB2461367B
公开(公告)日：2011-01-05
申请号：GB0908102
申请日：2009-05-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SNYDER TIMOTHY S , CUNHA FRANCISCO J
Abstract: A system comprises a bypass duct, a turbine case, a turbine exhaust ring and a splash plate. The turbine case is formed along a radially inner margin of the bypass duct, and the turbine exhaust ring is coaxially disposed within the turbine case. The splash plate extends axially along the turbine exhaust ring, radially spaced between the turbine exhaust ring and the turbine case. There are cooling fluid apertures in the turbine case to provide cooling fluid flow from the bypass duct onto the splash plate, and impingement holes in the splash plate to provide impingement flow onto the turbine exhaust ring.
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公开(公告)号：SG144719A1
公开(公告)日：2008-08-28
申请号：SG2004027124
申请日：2004-04-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SNYDER TIMOTHY S , BRDAR CHRISTOPHER R , BUEY JOHN R
Abstract: AUGMENTOR PILOT NOZZLE A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.
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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
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.
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