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    TURBINE NOZZLE AIRFORIL AND/OR TRAILING EDGE PROFILE
    11.
    发明申请
    TURBINE NOZZLE AIRFORIL AND/OR TRAILING EDGE PROFILE 有权

    公开(公告)号：US20210277787A1

    公开(公告)日：2021-09-09

    申请号：US16812506

    申请日：2020-03-09

    Applicant: General Electric Company

    Inventor： Alexander Stein ,  Jacob John Kittleson ,  Daniel Robert Burnos

    IPC: F01D9/02

    Abstract: A turbine nozzle for a gas turbine includes: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs that define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the airfoil profile sections at the Z distances are joined smoothly with one another to form the nominal profile. A trailing edge profile for a turbine nozzle is also disclosed.

    Method for making cooling assembly for a turbomachine part
    12.
    发明授权
    Method for making cooling assembly for a turbomachine part 有权

    公开(公告)号：US10717101B2

    公开(公告)日：2020-07-21

    申请号：US15898285

    申请日：2018-02-16

    Applicant: General Electric Company

    Inventor： Tyler Christopher Henson ,  Jacob John Kittleson ,  Lauren Alexandra Schuhle

    IPC: B05D1/32 ,  B05B12/26 ,  F01D5/18 ,  F01D5/28

    Abstract: A method of forming a cooling assembly in a turbomachine part is provided. The method includes placing an encapsulated diffuser insert partially into a hole in the turbomachine part. The encapsulated diffuser insert has an unobstructed central passageway with a generally circular cross-section at a first end and an elongated rectangular cross-section at a second end opposing the first end. The second end has a sacrificial cap. A coating step coats the turbomachine part to at least partially encapsulate the encapsulated diffuser insert in a coating. A removing step removes the sacrificial cap to enable air flow through the central passageway. The encapsulated diffuser insert remains in the hole of the turbomachine part and the coating, thereby providing the unobstructed central passageway with a generally circular first end and an elongated rectangular second end adjacent to an outer surface of the turbomachine part.

    Seals With Cooling Pathways and Metered Cooling
    15.
    发明申请
    Seals With Cooling Pathways and Metered Cooling 有权
    密封件具有冷却通道和计量冷却

    公开(公告)号：US20160319685A1

    公开(公告)日：2016-11-03

    申请号：US14697765

    申请日：2015-04-28

    Applicant: General Electric Company

    Inventor： Matthew Troy Hafner ,  Victor John Morgan ,  Jacob John Kittleson ,  Neelesh N. Sarawate

    IPC: F01D11/00 ,  F01D25/12 ,  F02C7/18 ,  F16J15/06

    CPC classification number: F01D11/005 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/20 ,  F16J15/064

    Abstract: The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path.

    Abstract translation: 本申请提供了在面向高压冷却空气流的部件发动机和燃气涡轮机中的热气体路径之间使用的密封件。 密封件可以包括第一垫片，具有空气出口孔的第二垫片，位于第一垫片和第二垫片之间的一个或多个中间层，以及延伸穿过用于高压冷却空气流的中间层的一个或多个冷却路径 通过空气出口孔流入热气路径。

    Nozzle with slash face(s) with swept surfaces joining at arc with peak aligned with stiffening member
    16.
    发明授权
    Nozzle with slash face(s) with swept surfaces joining at arc with peak aligned with stiffening member 有权

    公开(公告)号：US11492917B2

    公开(公告)日：2022-11-08

    申请号：US16793266

    申请日：2020-02-18

    Applicant: General Electric Company

    Inventor： Jacob John Kittleson ,  Robert Frank Hoskin

    IPC: F01D9/04 ,  F01D5/14

    Abstract: A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at an arc having a peak that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.

    NOZZLE WITH SLASH FACE(S) WITH SWEPT SURFACES WITH JOINING LINE ALIGNED WITH STIFFENING MEMBER
    18.
    发明申请
    NOZZLE WITH SLASH FACE(S) WITH SWEPT SURFACES WITH JOINING LINE ALIGNED WITH STIFFENING MEMBER 有权

    公开(公告)号：US20210254472A1

    公开(公告)日：2021-08-19

    申请号：US16793269

    申请日：2020-02-18

    Applicant: General Electric Company

    Inventor： Jacob John Kittleson

    IPC: F01D5/14 ,  F01D9/04

    Abstract: A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at a joining line that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.

    Preform CMC article, CMC article, and method for forming CMC article
    19.
    发明授权
    Preform CMC article, CMC article, and method for forming CMC article 有权

    公开(公告)号：US10533432B2

    公开(公告)日：2020-01-14

    申请号：US15421882

    申请日：2017-02-01

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Jacob John Kittleson ,  James Murray ,  Gregory Scot Corman

    IPC: B32B5/26 ,  F01D5/28

    Abstract: A preform CMC article is disclosed comprising an interior ply structure having at least one interior CMC ply including at least one longitudinal CMC ply disposed along the article length, an exterior shell ply forming an article surface and having at least one exterior CMC ply substantially surrounding the interior ply structure, and at least one wicking portion in which the interior ply structure penetrates the exterior ply shell with an exposed edge of the longitudinal CMC ply disposed at the article surface. A CMC article is disclosed including the interior ply structure and the exterior ply shell, wherein the longitudinal CMC ply includes an exposed edge disposed at the surface of the CMC article. A method for forming the CMC article is disclosed including wicking a melt infiltration agent into the article through the wicking portion into the interior ply structure along the longitudinal CMC ply.

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