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公开(公告)号：US11112115B2
公开(公告)日：2021-09-07
申请号：US14910827
申请日：2014-06-30
发明人： Stanislav Kostka, Jr. , Randal G. McKinney , James B. Hoke , Timothy S. Snyder , Frank J. Cunha
摘要： A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.
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公开(公告)号：US10697636B2
公开(公告)日：2020-06-30
申请号：US15100374
申请日：2014-12-04
摘要： An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.
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公开(公告)号：US10670268B2
公开(公告)日：2020-06-02
申请号：US14893378
申请日：2014-05-23
发明人： Frank J. Cunha , Stanislav Kostka
摘要： A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors which extend from a cold side thereof. At least one of the multiple of heat transfer augmentors includes a first heat transfer augmentation feature with a second heat transfer augmentation feature stacked thereon.
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公开(公告)号：US10598379B2
公开(公告)日：2020-03-24
申请号：US15034689
申请日：2014-11-25
摘要： An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.
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公开(公告)号：US10533745B2
公开(公告)日：2020-01-14
申请号：US15113558
申请日：2015-02-03
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.
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公开(公告)号：US10443848B2
公开(公告)日：2019-10-15
申请号：US14677520
申请日：2015-04-02
摘要： A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.
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公开(公告)号：US10378768B2
公开(公告)日：2019-08-13
申请号：US15037555
申请日：2014-12-04
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.
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公开(公告)号：US20160298843A1
公开(公告)日：2016-10-13
申请号：US15100374
申请日：2014-12-04
摘要： An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.
摘要翻译： 提供了一种用于涡轮发动机的组件。 涡轮发动机组件的燃烧器壁包括外壳和隔热罩。 燃烧器壁限定了通过壳体和隔热罩的淬火孔。 热屏蔽限定了与骤冷孔的距离等于渗出口宽度的大约二十五倍到七十五倍之间的渗出口。
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公开(公告)号：US20160265774A1
公开(公告)日：2016-09-15
申请号：US15032190
申请日：2014-11-21
CPC分类号： F23R3/002 , F02C7/18 , F02C7/24 , F05D2220/32 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , F05D2260/231 , F23M5/085 , F23R3/005 , F23R3/007 , F23R3/06 , F23R3/44 , F23R2900/00017 , F23R2900/03042 , F23R2900/03044 , F23R2900/03045
摘要： A multi-walled structure is provided for a turbine engine. This structure includes a shell with a textured first surface, and a heat shield with a second surface. The heat shield is attached to the shell. The first and the second surfaces vertically define a cooling cavity between the shell and the heat shield. The cooling cavity fluidly couples a plurality of cooling apertures defined in the shell with a plurality of cooling apertures defined in the heat shield.
摘要翻译： 为涡轮发动机提供多壁结构。 该结构包括具有纹理化第一表面的外壳和具有第二表面的隔热罩。 隔热罩安装在外壳上。 第一和第二表面垂直地限定了壳体与隔热罩之间的冷却腔。 冷却腔将限定在外壳中的多个冷却孔与限定在隔热罩中的多个冷却孔流体耦合。
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公开(公告)号：US20160252249A1
公开(公告)日：2016-09-01
申请号：US15026761
申请日：2014-10-06
发明人： Nurhak Erbas-Sen , Frank J. Cunha
CPC分类号： F23R3/002 , F23R3/06 , F23R3/08 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity fluidly couples apertures defined in the shell with the second cavity. The second cavity fluidly couples the first cavity with apertures defined in the heat shield. The shell and the heat shield converge toward one another about the second cavity.
摘要翻译： 为涡轮发动机提供燃烧器壁，并且包括燃烧器外壳和隔热罩。 隔热罩安装在外壳上，第一和第二腔在外壳和隔热罩之间延伸。 第一凹腔将壳体中限定的孔与第二腔流体耦合。 第二腔体将第一空腔与限定在隔热罩中的孔流体连接。 壳体和隔热罩围绕第二腔室彼此会聚。
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