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    CIRCUMFERENTIALLY AND AXIALLY STAGED ANNULAR COMBUSTOR FOR GAS TURBINE ENGINE COMBUSTOR
    11.
    发明申请
    CIRCUMFERENTIALLY AND AXIALLY STAGED ANNULAR COMBUSTOR FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    燃气涡轮发动机燃烧室的圆周和轴向环形燃烧室

    公开(公告)号：WO2015108583A3

    公开(公告)日：2015-10-01

    申请号：PCT/US2014061532

    申请日：2014-10-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER TIMOTHY S

    IPC: F23R3/28 ,  F02C7/22 ,  F23R3/42

    CPC classification number: F23R3/346 ,  F23R3/002 ,  F23R3/06 ,  F23R3/14 ,  F23R3/50 ,  Y02T50/675

    Abstract: A combustor section for a gas turbine engine includes an outer wall assembly and an inner wall assembly inboard of the outer wall assembly to define an annular combustion chamber therebetween. A forward fuel injection system is in communication with the combustion chamber. A downstream fuel injection system is in communication with the combustion chamber through the outer wall assembly and a swirl mixer system in communication with the combustion chamber through the inner wall assembly.

    Abstract translation: 用于燃气涡轮发动机的燃烧器部分包括外壁组件和在外壁组件内侧的内壁组件，以在其间限定环形燃烧室。 前燃料喷射系统与燃烧室连通。 下游燃料喷射系统通过外壁组件和通过内壁组件与燃烧室连通的涡流混合器系统与燃烧室连通。

    14.
    发明专利
    未知

    公开(公告)号：NO20041951L

    公开(公告)日：2004-11-15

    申请号：NO20041951

    申请日：2004-05-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BUEY JOHN R ,  SNYDER TIMOTHY S ,  BRDAR CHRISTOPHER R

    IPC: F02K3/00 ,  F02K3/10 ,  F23D11/12 ,  F23R3/20 ,  F23R3/28 ,  F02K1/10 ,  F02K1/00 ,  F02K1/30

    Abstract: A gas turbine engine augmentor (72) nozzle has an inlet (104) for connection to an augmentor fuel conduit and an outlet (106) for expelling a spray of fuel. A passageway (110) between the inlet (104) and outlet (106) is at least partially bounded by outlet end surface portions (126,128) diverging from each other. The nozzle (70) may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline (150) toward radial.

    15.
    发明专利
    未知

    公开(公告)号：DE60216168D1

    公开(公告)日：2007-01-04

    申请号：DE60216168

    申请日：2002-02-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER TIMOTHY S

    IPC: F23R3/06 ,  F23C99/00 ,  F23R3/00 ,  F23R3/10

    Abstract: A combustor for a gas turbine engine includes inner and outer liners 32,34 with a row 112, 114 of dilution air holes penetrating through each liner. The row 114 of holes in the outer liner 34 comprise at least a set of large size, major outer holes 116 and may also include a set of smaller size minor outer holes 118 circumferentially intermediate neighboring pairs of the major outer holes 116. The row 112 of holes in the inner liner include dilution air holes circumferentially offset from the major outer holes 116 and may also include a set of minor holes 122 circumferentially intermediate major inner holes 120. The major and minor holes admit respective major and minor jets of dilution air into the combustor. The distribution of major and minor holes and the corresponding major and minor dilution air jets helps to minimize NOx emissions and regulates the spatial temperature profile of the exhaust gases discharged from the combustor.

    INJECTOR WITH TWO-FLOW TANGENTIAL ENTRY AND SEPARATED FLAME
    16.
    发明专利
    INJECTOR WITH TWO-FLOW TANGENTIAL ENTRY AND SEPARATED FLAME 未知

    公开(公告)号：RU2193686C2

    公开(公告)日：2002-11-27

    申请号：RU97121010

    申请日：1997-12-19

    Applicant: UNITED TECHNOLOGIES CORP ,  TATA DELAWARE

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

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

    Abstract: FIELD: power engineering. SUBSTANCE: proposed injector has longitudinal axis and two spiral elements with cylindrical dome, axial lines of elements being displaced relative to each other. Overlapping ends of elements form inlet slot to feed fuel-air mixture into injector. End face plate of combustion chamber is provided with central hole to feed fuel and air into combustion chamber while other opposite end face plate blocks area of injector flow. Spiral elements are secured between said end face plates. Central part is located between said elements coaxially relative to longitudinal axis and it has base with at least one hole to deliver air passing through hole and inner channel, and also truncated figure section and aerodynamically shaped inclined sections preventing formation of reverse flow and providing stabilization of flame between said end face plates. EFFECT: increased service life. 6 cl, 3 dwg

    BLUFF BODY PREMIXING FUEL INJECTOR AND METHOD FOR PREMIXING FUEL AND AIR
    18.
    发明专利
    BLUFF BODY PREMIXING FUEL INJECTOR AND METHOD FOR PREMIXING FUEL AND AIR 未知

    公开(公告)号：CA2255549A1

    公开(公告)日：1999-06-15

    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: F23R3/30 ,  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 combust or 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 config ured to inject a primary fuel nonuniformly along the length of the air entry slots and t o control the fuel penetration depth d in proportion to slot height H. The injector also inclu des a flame disgorging centerbody (48) having a bluff tip (54) longitudinally aligned with t he injector's discharge plane (22) and a secondary fuel conduit (80) extending through the cen terbody 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 i mproves fuel injector durability by resisting ingestion of combustion flame into the mix ing chamber (28) and reliably disgorging any flame that is ingested. The controlled fuel pe netration 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 alignmen t with the fuel injector discharge plane, makes the centerbody capable of anchoring the fla me at the discharge plane so that combustion occurs aft of the discharge plane where the combustion flame is unlikely to damage the scrolls or centerbody. Introduction 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 longitudin ally nonuniform injection of primary fuel compensates for any mixing nonuniformities attributable to the flame disgorging centerbody and therefore augments flame sta bility. The injector and an associated method of premixing fuel and air prior to combust ion suppress formation of nitrous oxides, and improve the durability of both the inj ector and the combustor.

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