中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

63 records (took 0.022 seconds)

    METHOD FOR BURNING FUEL BY FUEL INJECTOR AND COMBUSTOR
    1.
    发明专利
    METHOD FOR BURNING FUEL BY FUEL INJECTOR AND COMBUSTOR 失效

    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.

    COMBUSTOR FOR TURBINE ENGINE
    3.
    发明专利
    COMBUSTOR FOR TURBINE ENGINE 有权

    公开(公告)号：JP2002267161A

    公开(公告)日：2002-09-18

    申请号：JP2002049039

    申请日：2002-02-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER TIMOTHY S

    IPC: F23C99/00 ,  F23R3/00 ,  F23R3/06 ,  F23R3/10 ,  F23C11/00

    Abstract: PROBLEM TO BE SOLVED: To reduce the discharging amount of NOx of a combustor for a gas turbine engine and optimize the spatial temperature profile of exhaust gas. SOLUTION: Rows of combustion air inlets are provided on the inside liner 32 of a combustion chamber 36 and the circumferential direction of an outside liner 34. The row of combustion air inlets in the outside liner 34 is provided with a primary outside inlets 116 having a large size and small-sized secondary inside inlets 118 between mutually neighbored primary outside inlets 116. The primary injection stream of combustion air penetrates inside radially by the primary outside inlets 116 while the secondary injection stream of the combustion air penetrates inside radially by a small distance by the secondary inside inlets 118 whereby the primary injection stream is compensated. The primary inside inlets 120 is separated radially from the primary outside inlets. The injection stream of combustion air penetrates outside radially by the primary inside inlets 120. The inside inlets and the outside inlets are distributed in such a manner whereby fuel is mixed perfectly into air.

    FUEL NOZZLE ASSEMBLY
    4.
    发明专利
    FUEL NOZZLE ASSEMBLY 失效

    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.

    FUEL NOZZLE ASSEMBLY
    5.
    发明专利
    FUEL NOZZLE ASSEMBLY 失效

    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.

    COMBUSTOR BULKHEAD COOLING ARRAY
    7.
    发明申请
    COMBUSTOR BULKHEAD COOLING ARRAY 审中-公开
    COMBUSTOR BULKHEAD冷却阵列

    公开(公告)号：WO2014084942A3

    公开(公告)日：2015-03-26

    申请号：PCT/US2013057047

    申请日：2013-08-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER TIMOTHY S ,  TU JOHN S

    IPC: F02C1/00

    CPC classification number: F23R3/002 ,  F23R3/04 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A bulkhead panel is disclosed. The bulkhead panel may comprise a body having a body having a front surface and an opposite back surface, a fuel nozzle opening in the body and communicating through the front and back surfaces, and a plurality of effusion holes disposed in at least one row that surrounds and is generally concentric to the fuel nozzle opening. Each effusion hole may extend from the back surface to the front surface at an incline angle. Each effusion hole may be positioned at a clock angle from a reference line radially extending from a center of the fuel nozzle opening through a center of the effusion hole.

    Abstract translation: 公开了一种隔板。 舱壁板可以包括具有主体的主体，该主体具有前表面和相对的后表面，在主体中的燃料喷嘴开口并通过前表面和后表面连通，并且多个排出孔设置在至少一排中， 并且通常与燃料喷嘴开口同心。 每个渗出孔可以以倾斜角从后表面延伸到前表面。 每个渗出孔可以从从燃料喷嘴开口的中心径向延伸穿过渗出孔的中心的参考线以时钟角定位。

    CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    10.
    发明申请
    CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    燃气轮机发动机燃油通风的CO-SWIRL方向

    公开(公告)号：WO2015126501A3

    公开(公告)日：2015-10-22

    申请号：PCT/US2014068377

    申请日：2014-12-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TU JOHN S ,  SNYDER TIMOTHY S ,  HOKE JAMES B ,  BANGERTER JAMES P ,  DUHAMEL DENNIS J ,  BURNS DAVID A

    IPC: F23R3/12 ,  F23R3/26 ,  F23R3/42

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.

    Abstract translation: 用于燃气涡轮发动机的燃烧器中的衬板包括一个包括多个喷射通道的前部区域，每个喷射通道以与燃烧气体的局部涡流方向一致的方向指向。 用于燃气涡轮发动机的燃烧器中的另一衬套面板包括稀释通道前方的前部区域和前部区域的后部后部区域。 前部区域包括多个通常沿周向引导的排出通道。 后部区域包括多个通过轴向大致定向的排出通道。 一种冷却燃气涡轮发动机的燃烧器内的壁组件的方法包括在与燃烧气体的局部涡流方向一致的前向区域内定向多个排出通道。

Patent Agency Ranking