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    DILUTION HOLE ASSEMBLY
    136.
    发明申请
    DILUTION HOLE ASSEMBLY 有权
    稀释孔组件

    公开(公告)号：US20160003478A1

    公开(公告)日：2016-01-07

    申请号：US14789557

    申请日：2015-07-01

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, JR. ,  Stanislav Kostka, JR.

    IPC: F23R3/14 ,  F23R3/00

    CPC classification number: F23R3/14 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A dilution hole assembly that may be of a combustor has a first wall that defines a hole that may communicate through a liner and outer shell of the combustor for flowing dilution air from an air plenum located outward of the shell and into a combustion chamber defined by and located inward of the liner. The assembly has an outer wall that may be engaged to the shell and liner, and which defines the hole. An inner wall of the assembly may be in the hole such that an annular portion of the hole is defined between the inner and outer walls. A plurality of vanes may be in the annular portion and spaced from one-another for swirling air that flows through the annular portion. The walls may be generally conical in shape and/or radially sloped such that air flowing through the annular portion and air flowing at least through the inner portion impinge upon one-another adding to the air turbulence created by the swirling action of the vanes and thus enhancing efficient combustion and temperature profiling within the combustion chamber.

    Abstract translation: 可以是燃烧器的稀释孔组件具有第一壁，其限定可以通过燃烧器的衬套和外壳连通的孔，用于将稀释空气从位于壳体外部的空气室排出并进入由壳体外部限定的燃烧室 并位于内衬的内侧。 组件具有外壁，其可以接合到壳体和衬套，并且限定孔。 组件的内壁可以在孔中，使得孔的环形部分限定在内壁和外壁之间。 多个叶片可以在环形部分中并且彼此间隔开以流过环形部分的旋转空气。 壁可以是大致圆锥形的和/或径向倾斜的，使得流过环形部分的空气和至少通过内部部分流动的空气彼此撞击，从而增加由叶片的旋动作用产生的空气湍流，因此 提高燃烧室内的有效燃烧和温度分布。

    BLADES AND BLADE DAMPERS FOR GAS TURBINE ENGINES
    137.
    发明申请
    BLADES AND BLADE DAMPERS FOR GAS TURBINE ENGINES 有权
    用于气体涡轮发动机的叶片和叶片阻尼器

    公开(公告)号：US20150330227A1

    公开(公告)日：2015-11-19

    申请号：US14639490

    申请日：2015-03-05

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley

    IPC: F01D5/16

    CPC classification number: F01D5/16 ,  F01D5/22 ,  F01D11/006 ,  F05D2250/75

    Abstract: A blade damper for a gas turbine blade includes a blade damper body with a first damping surface and a second damping surface. The first damping surface is on a first side of the damper body and the second damping surface is on a second side of the damper body opposite the first damping surface for providing full functionality in both flipped and unflipped orientations.

    Abstract translation: 用于燃气轮机叶片的叶片阻尼器包括具有第一阻尼表面和第二阻尼表面的叶片阻尼器本体。 第一阻尼表面位于阻尼器本体的第一侧上，第二阻尼表面位于阻尼器主体的与第一阻尼表面相对的第二侧上，用于在翻转和未翻转的取向中提供全部功能。

    Airfoil with wall that tapers in thickness
    138.
    发明授权
    Airfoil with wall that tapers in thickness 有权

    公开(公告)号：US11753944B2

    公开(公告)日：2023-09-12

    申请号：US16594353

    申请日：2019-10-07

    Applicant: United Technologies Corporation

    Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

    IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/201 ,  F05D2260/204

    Abstract: An airfoil section has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The airfoil wall circumscribes an internal core cavity. A skincore passage is embedded in the first side of the airfoil wall between inner and outer portions of the first side of airfoil wall. The skincore passage defines a passage forward edge and a passage aft edge. The first side of the airfoil wall has a portion that tapers in thickness at the passage aft edge. A cooling passage is embedded in the second side of the airfoil wall between inner and outer portions of the second side of airfoil wall. The inner portion of the second side of the airfoil wall includes a protrusion located across the internal core cavity from the portion of the first side that tapers in thickness.

    Airfoil with convex sides and multi-piece baffle
    139.
    发明授权
    Airfoil with convex sides and multi-piece baffle 有权

    公开(公告)号：US11661850B2

    公开(公告)日：2023-05-30

    申请号：US16532626

    申请日：2019-08-06

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley

    IPC: F01D5/14

    CPC classification number: F01D5/141 ,  F05D2220/32 ,  F05D2240/126 ,  F05D2250/711

    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second convex sides that join the leading end and the trailing end. The first and second convex sides span in a longitudinal direction between first and second ends. The first and second convex sides define lateral bounds of an internal core cavity, and the first and second convex sides converge toward each other at each of the first and second ends such that the internal core cavity constricts at the first and second ends. A multi-piece baffle is disposed in the internal core cavity and has a shape that is complementary to the first and second convex sides.

    Article having cooling passage network with inter-row sub-passages
    140.
    发明授权
    Article having cooling passage network with inter-row sub-passages 有权

    公开(公告)号：US11333023B2

    公开(公告)日：2022-05-17

    申请号：US16594224

    申请日：2019-10-07

    Applicant: United Technologies Corporation

    Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

    IPC: F01D5/18 ,  F01D5/08 ,  F01D9/06

    Abstract: A gas turbine engine article includes a cooling passage network embedded in an article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from a cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The array of pedestals includes first pedestals arranged in a first row and second pedestals arranged in a second, adjacent row. The first pedestals and the second pedestals define inter-row sub-passages there between. Each of the inter-row sub-passages has an inlet mouth, an outlet mouth, and a compound channel connecting the inlet mouth and the outlet mouth. The compound channel includes a first channel length over which the inter-row sub-passage has a constant cross-section and a second channel length over which the inter-row sub-passage has a non-constant cross-section.

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