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公开(公告)号：US20170009987A1
公开(公告)日：2017-01-12
申请号：US15113536
申请日：2015-02-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Randal G. McKinney , Frank J. Cunha , Stanislav Kostka, JR.
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.
Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括具有外壳和隔热罩的燃烧器壁。 燃烧器壁限定了通过其的淬火孔。 燃烧器壁还在外壳和隔热罩之间限定一个空腔。 壳体限定空气被引导到空腔中的第一孔。 隔热罩包括至少部分地限定第二孔的导轨，该第二孔构造成将空腔内的至少一些空气引导出燃烧器壁并且朝向骤冷孔。
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2.发明申请公开(公告)号：US20160265775A1
公开(公告)日：2016-09-15
申请号：US15034717
申请日：2014-11-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frank J. Cunha , Stanislav Kostka, JR.
Abstract: A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.
Abstract translation: 提供了一种用于涡轮发动机的结构。 该结构包括具有第一表面的外壳和具有带纹理的第二表面和纹理的第三表面的隔热罩。 第二表面的一部分的纹理不同于第三表面的一部分的质地。 第一表面和第二表面限定了壳体和隔热罩之间的第一冷却腔。 第一表面和第三表面在外壳和隔热罩之间限定第二冷却腔。
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公开(公告)号：US20160230662A1
公开(公告)日：2016-08-11
申请号：US14618298
申请日：2015-02-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Stanislav Kostka, JR. , Frank J. Cunha
CPC classification number: F02C7/18 , F01D5/187 , F01D25/08 , F05D2260/2212 , F05D2260/22141 , F23R3/005
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling scheme disposed inside the body portion, the cooling scheme including a vascular engineered lattice structure and a heat transfer device adjacent to the vascular engineered lattice structure.
Abstract translation: 根据本公开的示例性方面的部件包括布置在主体部分内部的主体部分和冷却方案，所述冷却方案包括血管工程格子结构和邻近血管工程格子的传热装置 结构体。
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公开(公告)号：US20170159935A1
公开(公告)日：2017-06-08
申请号：US15038906
申请日：2014-08-29
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Stanislav Kostka, JR. , Frank J. Cunha
CPC classification number: F23R3/002 , F01D25/12 , F02C7/18 , F05D2220/323 , F05D2230/60 , F05D2240/35 , F05D2260/201 , F05D2260/31 , F16B33/004 , F23R3/005 , F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
Abstract: A liner panel for use in a gas turbine engine. The liner panel has a hot side and a cold side. The liner panel includes a rail extending from the cold side and a multiple of studs extending from the cold side. At least one of the multiple of studs extends from, in part, the rail.
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公开(公告)号：US20170108220A1
公开(公告)日：2017-04-20
申请号：US15039071
申请日：2014-12-19
Applicant: United Technologies Corporation
Inventor： Stanislav Kostka, JR. , Frank J. Cunha
CPC classification number: F23R3/005 , F02C7/12 , F23R3/06 , F23R2900/03042
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell, a heat shield and an annular body. The body at least partially defines a first aperture through the shell and the heat shield. The body also defines one or more second apertures through which air is directed into the first aperture and provides non-uniform cooling to the body.
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Patent Agency Ranking
公开(公告)号：US20170009988A1
公开(公告)日：2017-01-12
申请号：US15113558
申请日：2015-02-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frank J. Cunha , Stanislav Kostka, JR.
Abstract: 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.
Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括包括外壳和隔热罩的燃烧器壁。 燃烧器壁限定壳体和隔热罩之间的第一和第二腔。 隔热罩限定第一出口和细长的第二出口。 第一出口与第一空腔流体耦合。 第二出口与第二腔流体耦合。 燃烧器壁限定一个具有锥形几何形状的空腔。
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公开(公告)号：US20160273772A1
公开(公告)日：2016-09-22
申请号：US15034702
申请日：2014-11-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frank J. Cunha , Stanislav Kostka, JR.
IPC: F23R3/00
CPC classification number: F23R3/002 , F05D2240/15 , F05D2260/201 , F23R3/005 , F23R3/06 , F23R2900/03044
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a body, a shell and a heat shield panel. The panel is attached to the shell with a tapered cooling cavity between the shell and the panel. The panel defines a cooling aperture configured to direct air out of the cooling cavity to impinge against the body.
Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括主体，壳体和隔热板。 面板在外壳和面板之间具有锥形冷却腔连接到外壳。 该面板限定了一个冷却孔，其构造成将空气引导出冷却腔以撞击身体。
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公开(公告)号：US20200240638A1
公开(公告)日：2020-07-30
申请号：US16827195
申请日：2020-03-23
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka, JR.
Abstract: 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：US20160377289A1
公开(公告)日：2016-12-29
申请号：US15038774
申请日：2014-12-03
Applicant: United Technologies Corporation
Inventor： Stanislav Kostka, JR. , Frank J. Cunha
CPC classification number: F23R3/005 , F05D2240/35 , F23R3/002 , F23R3/04 , F23R3/06 , F23R3/50 , F23R2900/00017 , F23R2900/03042 , F23R2900/03044
Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body defines a first cooling aperture fluidly coupled between a cooling cavity and the quench aperture. The cooling cavity is between the shell and the heat shield.
Abstract translation: 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壳体，隔热罩和环形体。 环形体延伸穿过燃烧器壁。 环形体至少部分地沿着穿过燃烧器壁的中心线限定了淬火孔。 环形体限定了流体耦合在冷却腔和淬火孔之间的第一冷却孔。 冷却腔位于外壳和隔热罩之间。
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10.发明申请公开(公告)号：US20160281986A1
公开(公告)日：2016-09-29
申请号：US14669206
申请日：2015-03-26
Applicant: United Technologies Corporation
Inventor： Hoyt Y. Chang , Christos Adamopoulos , Stanislav Kostka, JR.
CPC classification number: F23R3/002 , B22F3/1055 , B22F5/009 , B22F2003/1057 , B33Y10/00 , B33Y50/02 , B33Y80/00 , F23R3/007 , F23R3/06 , F23R3/50 , F23R2900/00018 , F23R2900/03042 , F23R2900/03043 , Y02T50/675
Abstract: A cooled wall for lining a combustor of a gas turbine engine includes an annular outer wall defining a radial passage extending therethrough, an inner wall spaced radially from the outer wall to define an axial channel in fluid communication with the radial passage, and a connecting wall joining the inner wall to the outer wall. A method of making the cooled wall includes providing a three-dimensional computer model of the cooled wall, depositing a uniform thickness layer of material on a substrate, using a laser or electron beam to melt or sinter the material to form a cross section, repeating the depositing and cross section steps to form the cooled wall, and heat treating the cooled wall.
Abstract translation: 用于衬套燃气涡轮发动机的燃烧器的冷却壁包括限定通过其延伸的径向通道的环形外壁，与外壁径向间隔开的内壁，以限定与径向通道流体连通的轴向通道，以及连接壁 将内壁连接到外壁。 制造冷却壁的方法包括提供冷却壁的三维计算机模型，使用激光或电子束在衬底上沉积均匀的厚度的材料层以熔化或烧结材料以形成横截面，重复 沉积和横截面步骤以形成冷却的壁，并且对冷却的壁进行热处理。
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