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公开(公告)号：US10774685B2
公开(公告)日：2020-09-15
申请号：US15966760
申请日：2018-04-30
摘要： A heat shield for a gas turbine engine includes a radial heat shield flange that extends in a circumferential direction and forms a ring. A plurality of bosses extend from a first axial side of the radial heat shield flange. There is a plurality of guide pins. One of the plurality of guide pins extends from a corresponding one of the plurality of bosses.
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公开(公告)号：US10551065B2
公开(公告)日：2020-02-04
申请号：US15165003
申请日：2016-05-26
发明人： Jonathan Jeffery Eastwood , Joey Wong , Robert M. Sonntag , Albert K. Cheung , Timothy S. Snyder
摘要： A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.
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公开(公告)号：US20190078457A1
公开(公告)日：2019-03-14
申请号：US15700264
申请日：2017-09-11
发明人： Jonathan Jeffery Eastwood , Joseph F. Englehart , Christopher Carter Venable , Michael G. McCaffrey
摘要： A gas turbine engine sealing system includes a case including forward and aft hooks. The aft hook arranged radially outward of the forward hook. A blade outer air seal has a J-hook that receives the aft hook and includes an end received by the forward hook.
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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：US20160273773A1
公开(公告)日：2016-09-22
申请号：US15165003
申请日：2016-05-26
发明人： Jonathan Jeffery Eastwood , Joey Wong , Robert M. Sonntag , Albert K. Cheung , Timothy S. Snyder
摘要： A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.
摘要翻译： 燃气涡轮发动机包括风扇，压缩机部分，燃烧器，风扇驱动齿轮系统和联接成通过齿轮系驱动风扇的涡轮部分。 燃烧器包括环形外壳和限定环形燃烧室的环形内壳。 在环形燃烧室中有一个隔壁，并在隔板上安装一个环形隔热罩。 环形隔热罩包括具有前表面和后表面，周向外侧和周向内侧的区段，前表面和后表面之间的中心孔，从中心孔周围的前表面突出的唇部 ，从前表面突出的轨道，以及轨道和唇缘之间的多个通孔。 轨道接触隔板以限定由轨道，唇缘和舱壁限定的空腔。
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公开(公告)号：US10670269B2
公开(公告)日：2020-06-02
申请号：US15334860
申请日：2016-10-26
摘要： A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused gate blended into a hot side of the liner panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused gate blended into a hot side of the liner panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused gate tangentially cast into a hot side of a liner panel; and applying a thermal barrier coating to the hot side of the liner panel over the remnant of the radiused gate.
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公开(公告)号：US10519811B2
公开(公告)日：2019-12-31
申请号：US15284763
申请日：2016-10-04
摘要： A flange heat shield is provided. The flange heat shield may comprise an annular body having a forward end opposite an aft end. The forward end of the flange heat shield may comprise a radial snap configured to interface with an inner surface of an engine case. The inner surface of the engine case may comprise an airflow ramp forward of the radial snap. The aft end of the flange heat shield may comprise a plurality of notches defining voids on the aft end. The aft end of the flange heat shield may also comprise mounting tabs configured to couple the flange heat shield to the engine case.
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公开(公告)号：US20180094545A1
公开(公告)日：2018-04-05
申请号：US15284763
申请日：2016-10-04
摘要： A flange heat shield is provided. The flange heat shield may comprise an annular body having a forward end opposite an aft end. The forward end of the flange heat shield may comprise a radial snap configured to interface with an inner surface of an engine case. The inner surface of the engine case may comprise an airflow ramp forward of the radial snap. The aft end of the flange heat shield may comprise a plurality of notches defining voids on the aft end. The aft end of the flange heat shield may also comprise mounting tabs configured to couple the flange heat shield to the engine case.
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公开(公告)号：US20160169514A1
公开(公告)日：2016-06-16
申请号：US14930757
申请日：2015-11-03
CPC分类号： F23R3/002 , F01D9/023 , F01D9/041 , F01D9/042 , F01D9/047 , F01D25/24 , F02C7/20 , F23R3/04 , F23R3/10 , Y02T50/671
摘要： An inner casing for a diffuser-combustor assembly of a gas turbine engine is disclosed. The inner casing may include an outer-ring, an inner-ring circumscribed by the outer-ring, and a strut having a body extending between the inner-ring and the outer-ring. In addition, the inner casing may include a reinforcing-pad.
摘要翻译： 公开了一种用于燃气涡轮发动机的扩散器 - 燃烧器组件的内壳。 内壳体可以包括外圈，由外圈包围的内圈，以及在内圈和外圈之间延伸的主体的支柱。 另外，内壳可以包括加强垫。
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公开(公告)号：US20160169245A1
公开(公告)日：2016-06-16
申请号：US14935628
申请日：2015-11-09
CPC分类号： F04D29/542 , F01D9/023 , F01D9/041 , F01D11/005 , F04D29/083 , F05D2220/3219 , F05D2230/642 , F05D2260/36
摘要： A pre-diffuser and exit guide vane (EGV) system for a gas turbine engine includes an annular EGV assembly containing a number of guide vanes and having an annular opening bounded by a radially inner annular sealing surface at a first radius and a radially outer annular sealing surface at a second radius. First and second seals substantially matching the first and second radii respectively join the EGV assembly to an annular pre-diffuser having an annular opening bounded by radially inner and outer annular sealing surfaces at substantially the first and second radii. The seals seal the inner sealing surface of the EGV assembly to the inner sealing surface of the pre-diffuser and the second seal seals the outer sealing surface of the EGV assembly to the outer sealing surface of the pre-diffuser, such that the EGV assembly annular opening is in fluid communication with the annular opening of the pre-diffuser.
摘要翻译： 用于燃气涡轮发动机的预扩散器和出口导叶（EGV）系统包括环形EGV组件，其包含多个导向叶片，并且具有环形开口，该环形开口由第一半径处的径向内部环形密封表面限定，并且径向外部环形 密封表面在第二个半径。 基本上匹配第一和第二半径的第一和第二密封分别将EGV组件连接到环形预扩散器，该环形预扩散器具有基本上第一和第二半径处的径向内部和外部环形密封表面限定的环形开口。 密封件将EGV组件的内部密封表面密封到预扩散器的内部密封表面，并且第二密封件将EGV组件的外部密封表面密封到预扩散器的外部密封表面，使得EGV组件 环形开口与预扩散器的环形开口流体连通。
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