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公开(公告)号：US20180347373A1
公开(公告)日：2018-12-06
申请号：US16000239
申请日：2018-06-05
CPC分类号： F01D5/186 , F01D9/02 , F01D9/041 , F01D11/08 , F01D25/12 , F04D29/526 , F04D29/5846 , F05D2220/32 , F05D2230/21 , F05D2230/30 , F05D2250/28 , F05D2260/202 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , Y02T50/673 , Y02T50/676
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole with respect to a dimension of the component to communicate additional fluid into the hollow vascular engineered lattice structure.
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公开(公告)号：US20180335212A1
公开(公告)日：2018-11-22
申请号：US15599196
申请日：2017-05-18
发明人： SAN QUACH , JEFFREY T. MORTON
CPC分类号： F23R3/002 , F02C7/18 , F05D2220/32 , F05D2230/00 , F05D2240/35 , F05D2260/201 , F23R3/42 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A combustor panel may include a body having an edge, a first endrail disposed along the edge of the body, and a second endrail disposed adjacent the first endrail, wherein a volume is defined between the first endrail and the second endrail. The first endrail may have a first height, measured from the body to a first tip of the first endrail, and the second endrail may have a second height, measured from the body to a second tip of the second endrail, wherein the first height is the same as the second height. The second endrail may include an endrail hole extending through the second endrail.
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公开(公告)号：US20180306113A1
公开(公告)日：2018-10-25
申请号：US15491047
申请日：2017-04-19
发明人： Jeffrey T. Morton , San Quach
CPC分类号： F23R3/002 , F23R3/06 , F23R3/50 , F23R2900/00017 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： A combustor section of a turbine engine includes a first liner panel including a first end rail. The first end rail includes a protruding heat transfer feature. A second liner panel includes a second end rail disposed proximate the first end rail. The second end rail includes a recess matching the protruding heat transfer feature of the first end rail. A turbine engine and a method of assembling a combustor assembly of a gas turbine engine are also disclosed.
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公开(公告)号：US10072846B2
公开(公告)日：2018-09-11
申请号：US14791684
申请日：2015-07-06
发明人： Sarah Marie Monahan , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet
IPC分类号： F23R3/28 , F23R3/34 , F23C5/08 , F23R3/58 , F23R3/12 , F23R3/04 , F23C5/00 , F23R3/42 , F23C5/32 , F23R3/02 , F23R3/10 , F23C5/24 , F23R3/06
CPC分类号： F23R3/286 , F05D2240/35 , F23C5/00 , F23C5/08 , F23C5/10 , F23C5/24 , F23C5/32 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/10 , F23R3/12 , F23R3/34 , F23R3/346 , F23R3/42 , F23R3/58 , F23R2900/00015 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： A gas turbine engine and combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two axially spaced apart annular trapped vortex cavities are located on the combustor liner and staged axially and radially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities. A plurality of injectors are configured tangentially relative to circular radially outer wall extending between an aft wall and a forward wall of each cavity to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid.
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公开(公告)号：US10072845B2
公开(公告)日：2018-09-11
申请号：US14443160
申请日：2013-11-15
发明人： Joshua Tyler Mook , Michael Anthony Benjamin , David Richard Barnhart , Sean James Henderson , Ramon Martinez , Neerav Atul Patel , Mark Richard Shaw
CPC分类号： F23R3/283 , B23P6/005 , B23P15/00 , F02C7/18 , F23R3/14 , F23R2900/00005 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： An aft heat shield for a fuel nozzle tip includes: an annular shield wall; an annular shield flange extending radially outward from an aft end of the shield wall; an annular baffle flange surrounding the conical section, and disposed such that an axial gap is defined between the shield flange and the baffle flange, the baffle flange including a radially outer rim extending axially forward therefrom; and a plurality of impingement cooling holes passing through the baffle flange and oriented to as to direct air flow towards the shield wall.
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6.发明申请公开(公告)号：US20180231250A1
公开(公告)日：2018-08-16
申请号：US15348639
申请日：2016-11-10
发明人： Steven W. Burd
CPC分类号： F23M5/04 , F01D9/023 , F23M5/085 , F23R3/002 , F23R3/06 , F23R3/50 , F23R3/60 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A combustor for a gas turbine engine including a forward liner panel mounted to a support shell via a multiple of studs, the forward liner panel including an aft non-linear circumferential edge and an aft liner panel mounted to the support shell via a multiple of studs, the aft liner panel including a forward non-linear circumferential edge that is complementary to the aft non-linear circumferential edge.
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公开(公告)号：US20180128485A1
公开(公告)日：2018-05-10
申请号：US15343988
申请日：2016-11-04
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F23R2900/00017 , F23R2900/03042
摘要： A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a stud free zone downstream of a combustor swirler. A combustor for a gas turbine engine, the combustor including a liner panel mounted to the support shell via a multiple of studs, the liner panel including a stud free zone downstream of each respective combustor swirler, the stud free zone including a multiple of film cooling holes. A method of directing airflow through a wall assembly within a combustor of a gas turbine engine including providing a stud free zone in a forward liner panel downstream of a combustor swirler, the stud free zone including a multiple of film cooling holes.
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公开(公告)号：US09958160B2
公开(公告)日：2018-05-01
申请号：US14765222
申请日：2014-02-04
发明人： James A. Dierberger
CPC分类号： F23R3/06 , F01D25/12 , F01D25/30 , F05D2260/202 , F05D2260/4031 , F23R3/002 , F23R3/005 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/676
摘要： A component within a gas turbine engine includes a surface with one or more upstream-directed cooling film holes therethrough.
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公开(公告)号：US09851105B2
公开(公告)日：2017-12-26
申请号：US14790970
申请日：2015-07-02
发明人： Tracy A. Propheter-Hinckley , Dominic J. Mongillo , Joel H. Wagner , Mark F. Zelesky , Stanislav Kostka , Timothy S. Snyder
CPC分类号： F23R3/06 , F23R3/002 , F23R3/005 , F23R2900/00019 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.
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公开(公告)号：US09765968B2
公开(公告)日：2017-09-19
申请号：US13747938
申请日：2013-01-23
CPC分类号： F23R3/002 , F23R3/06 , F23R3/16 , F23R3/50 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y10T29/49231
摘要： A combustor is provided for a turbine engine. The combustor includes a first liner having a first side and a second side and a second liner having a first side and a second side. The second side of the second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second side of the first liner. The plurality of effusion cooling holes including a first effusion cooling hole extending from the first side to the second side with a non-linear line of sight.
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