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    APPARATUS AND METHOD FOR MITIGATING PARTICULATE ACCUMULATION ON A COMPONENT OF A GAS TURBINE
    1.
    发明申请
    APPARATUS AND METHOD FOR MITIGATING PARTICULATE ACCUMULATION ON A COMPONENT OF A GAS TURBINE 审中-公开

    公开(公告)号：US20190219268A1

    公开(公告)日：2019-07-18

    申请号：US16239911

    申请日：2019-01-04

    申请人： United Technologies Corporation

    发明人： Dennis M. Moura ,  Carey Clum

    IPC分类号： F23R3/08 ,  F23R3/04

    CPC分类号： F23R3/007 ,  F01D5/189 ,  F23R2900/03044

    摘要： A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection feature integrally formed in the first component and fluidly connecting a flow path located proximate to the second surface of first component to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway and into the cooling channel at least partially in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.

    Turbomachine
    2.
    发明申请
    Turbomachine 审中-公开

    公开(公告)号：US20190128138A1

    公开(公告)日：2019-05-02

    申请号：US16136313

    申请日：2018-09-20

    申请人： MAN Energy Solutions SE

    发明人： Robert Krewinkel

    IPC分类号： F01D25/12 ,  F23R3/00 ,  F01D9/06

    CPC分类号： F01D25/12 ,  F01D5/187 ,  F01D9/04 ,  F01D9/065 ,  F05D2250/141 ,  F05D2260/201 ,  F23R3/002 ,  F23R2900/03044

    摘要： A turbomachine, with a flow-conducting assembly, which on a first side serves for the flow-conduction of a first medium, which has a first temperature, and which on a second side is coolable with a second medium, which has a second temperature, that is lower than the first temperature, and with an impingement grille including openings which extend spaced from the flow-conducting assembly, wherein via the openings of the impingement grille the second medium is directable onto the second side of the flow-conducting assembly. In the region of at least some of the openings of the impingement grille, flow-conducting elements for the second medium are formed, which emanating from the impingement grille extend in the direction of the second side of the flow-conducting assembly to be cooled.

    COMBUSTION CHAMBER OF A TURBINE ENGINE
    5.
    发明申请
    COMBUSTION CHAMBER OF A TURBINE ENGINE 审中-公开

    公开(公告)号：US20180266690A1

    公开(公告)日：2018-09-20

    申请号：US15916061

    申请日：2018-03-08

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Patrice André Commaret ,  Romain Nicolas Lunel

    IPC分类号： F23R3/06 ,  F23R3/00 ,  F23R3/50

    CPC分类号： F23R3/06 ,  F23R3/005 ,  F23R3/10 ,  F23R3/50 ,  F23R2900/00012 ,  F23R2900/03044 ,  Y02T50/675

    摘要： An annular combustion chamber with an axis of revolution of a turbine engine delimited by coaxial inner and outer annular walls joined upstream by a substantially transverse bottom of the chamber, the chamber further comprising at least one annular deflector placed in the chamber and substantially parallel to the bottom of the chamber the bottom of the chamber having orifices designed to be passed through by the impact cooling air of the deflector and coming from upstream. The deflector is attached to the inner and outer walls in a sealed manner, and the cooling air of the deflector is discharged from the chamber through exhaust holes formed in the inner and outer walls.

    ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE
    8.
    发明申请
    ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180224123A1

    公开(公告)日：2018-08-09

    申请号：US15506404

    申请日：2014-09-05

    申请人： Siemens Aktiengesellschaft

    发明人： Matthias Hase ,  Sachin Terdalkar ,  Rajesh Rajaram

    IPC分类号： F23R3/00

    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 (10) is disclosed. The acoustic damping resonator system (10) 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 (24) 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.