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    GAS TURBINE COMBUSTION CHAMBER
    21.
    发明申请
    GAS TURBINE COMBUSTION CHAMBER 审中-公开

    公开(公告)号：US20170307217A1

    公开(公告)日：2017-10-26

    申请号：US15491116

    申请日：2017-04-19

    申请人： Rolls-Royce Deutschland Ltd & Co KG

    发明人： Carsten CLEMEN

    IPC分类号： F23R3/04 ,  F02C7/18 ,  F23R3/00

    CPC分类号： F23R3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

    摘要： A gas turbine combustion chamber with a double-wall embodiment, having an outer cold combustion chamber wall and an inner hot combustion chamber wall which form an intermediate space, with impingement cooling holes in the outer combustion chamber wall, effusion cooling holes in the inner combustion chamber wall, outer mixing holes in the outer combustion chamber wall, and inner mixing holes in the inner combustion chamber wall. Respectively, one tubular mixing element connects the outer mixing hole and the inner mixing hole, wherein the mixing element includes an inflow opening in its area which is arranged inside the intermediate space. The outer mixing hole has a smaller diameter than the inner mixing hole, and the throughflow surface area of the effusion holes that are adjoining the mixing element is reduced by the difference in surface area between the outer mixing hole and the inner mixing hole.

    TRANSITION DUCT ASSEMBLY WITH LATE INJECTION FEATURES
    24.
    发明申请
    TRANSITION DUCT ASSEMBLY WITH LATE INJECTION FEATURES 审中-公开

    公开(公告)号：US20170276368A1

    公开(公告)日：2017-09-28

    申请号：US15079091

    申请日：2016-03-24

    申请人： General Electric Company

    发明人： Jeffrey Scott LeBegue ,  Kevin Weston McMahan ,  James Scott Flanagan

    IPC分类号： F23R3/34 ,  F23R3/46 ,  F23R3/42

    CPC分类号： F23R3/346 ,  F23R3/425 ,  F23R3/46 ,  F23R2900/03041 ,  F23R2900/03044

    摘要： A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each of the plurality of transition ducts is offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly. The turbomachine includes a late injection assembly providing fluid communication for an injection fluid to flow into the interior downstream of the inlet of at least one transition duct of the plurality of transition ducts.

    ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE
    26.
    发明申请
    ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20170268777A1

    公开(公告)日：2017-09-21

    申请号：US15504686

    申请日：2014-09-05

    申请人： Siemens Aktiengesellschaft

    发明人： Matthias Hase ,  Sachin Terdalkar ,  Rajesh Rajaram ,  Clifford E. Johnson

    IPC分类号： F23R3/00 ,  F23M20/00

    CPC分类号： F23R3/002 ,  F23M20/005 ,  F23R2900/00014 ,  F23R2900/03044

    摘要： An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include one or more resonator chambers (18) that provide enhanced cooling with reduced risk of cracking and other damage. The resonator housing (18) may include resonator exhaust orifices (26) that are positioned closer to an area of maximum temperature within the combustor (12), thereby enabling the resonator (16) to reduce the temperature gradient within the combustor (12). The resonator housing (18) may be sized and configured to reduce stress found in conventional systems by increasing distances between resonator exhaust orifices (26) and between resonator inlet impingement orifices (30), among others.

    COMBUSTION CHAMBER
    27.
    发明申请
    COMBUSTION CHAMBER 审中-公开

    公开(公告)号：US20170241643A1

    公开(公告)日：2017-08-24

    申请号：US15421030

    申请日：2017-01-31

    申请人： ROLLS-ROYCE plc

    发明人： Thomas G MULCAIRE ,  Robert A HICKS ,  Marcus FOALE

    IPC分类号： F23R3/00 ,  F23R3/06

    CPC分类号： F23R3/002 ,  F23R3/007 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/03042 ,  F23R2900/03044

    摘要： A combustion chamber arrangement has an annular outer wall and an annular inner wall having an upstream row of tiles and a downstream row of tiles. The outer wall has a concave bend which is less than 175°. The downstream end of the upstream tiles and the upstream end of the downstream tiles are adjacent the concave bend. The downstream ends of the upstream tiles are spaced at a greater distance from the inner surface of the annular outer wall than the upstream end of the downstream tiles. The upstream tiles have curved lips extending in a downstream direction which overlap but are spaced radially from the upstream ends of the downstream tiles. The outer wall has a row of apertures to direct coolant onto the outer surfaces of the curved lips and the upstream tiles has a row of apertures extending to the inner surfaces of the curved lips.

    COMBUSTION DEVICE FOR GAS TURBINE ENGINE
    29.
    发明申请
    COMBUSTION DEVICE FOR GAS TURBINE ENGINE 审中-公开
    燃气轮机发动机燃烧装置

    公开(公告)号：US20170074521A1

    公开(公告)日：2017-03-16

    申请号：US15363105

    申请日：2016-11-29

    申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA

    发明人： Atsushi HORIKAWA ,  Masahide KAZARI ,  Kunio OKADA ,  Junichi KITAJIMA

    IPC分类号： F23R3/28 ,  F23R3/00

    CPC分类号： F23R3/286 ,  F02C7/232 ,  F23C2900/9901 ,  F23D2209/20 ,  F23R3/002 ,  F23R3/16 ,  F23R3/28 ,  F23R3/283 ,  F23R3/30 ,  F23R3/32 ,  F23R3/34 ,  F23R2900/03044 ,  Y02T50/675 ,  Y02T50/678

    摘要： A combustor includes: a combustion liner having a combustion chamber formed therein; a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion; and a supplemental burner. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel and air into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide groove that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

    摘要翻译： 燃烧器包括：具有形成在其中的燃烧室的燃烧衬套; 燃料喷射器，其安装到燃烧衬套的顶部，并且包括具有多个燃料喷射环形部分的燃料喷射构件和包括引导空气用于燃烧的多个燃烧空气环形部分的空气引导构件; 和补充燃烧器。 燃料喷射环形部分和燃烧空气环形部分同心地和交替地布置。 燃料喷射器将燃料和空气喷射到燃烧室中。 每个燃料喷射环形部分包括沿其径向开口的多个燃料喷射孔，并且每个燃烧空气环形部分包括在其轴向方向上敞开的多个空气引导槽，并且引导 从燃料喷射孔喷射的燃料的空气。

    INTERNALLY COOLED DILUTION HOLE BOSSES FOR GAS TURBINE ENGINE COMBUSTORS
    30.
    发明申请
    INTERNALLY COOLED DILUTION HOLE BOSSES FOR GAS TURBINE ENGINE COMBUSTORS 审中-公开
    用于气体涡轮发动机燃烧器的内部冷却空气泄漏孔

    公开(公告)号：US20170059162A1

    公开(公告)日：2017-03-02

    申请号：US14843197

    申请日：2015-09-02

    申请人： Pratt & Whitney Canada Corp.

    发明人： MICHAEL PAPPLE ,  SI-MAN AMY LAO ,  SRI SREEKANTH

    IPC分类号： F23R3/16 ,  F23R3/00

    CPC分类号： F23R3/16 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044 ,  F23R2900/03045

    摘要： A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.

    摘要翻译： 冷却装置围绕限定在燃气涡轮发动机的燃烧室的衬套中限定的稀释孔。 冷却装置包括从衬套的外表面围绕稀释孔突出的中空凸台。 空心凸台限定了围绕稀释孔周向延伸的内部空腔。 内腔具有与围绕衬套的空气压力室流体流动连通的入口和与燃烧室流体连通的出口。