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    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS INCLUDING VARIATION MODELING
    11.
    发明申请
    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS INCLUDING VARIATION MODELING 审中-公开

    公开(公告)号：US20200012751A1

    公开(公告)日：2020-01-09

    申请号：US16026627

    申请日：2018-07-03

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder ,  Kurt R. Heinemann ,  Glenn Levasseur

    IPC: G06F17/50

    Abstract: A method for qualifying a gas turbine engine component includes creating a first set of substantially identical gas turbine engine components via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component in the first set, and determining a variance model of the first set. The variance model includes a representative parameter profile, which includes a plurality of component parameter profiles. The sum of each of the component parameter profiles is the representative parameter profile. The method also includes determining at least one predicted response models based at least in part on the variance model, identifying as-manufactured parameters of a second engine component, applying the as-manufactured parameters of the second engine component to the at least one predicted response models, thereby generating a predicted response output, and qualifying the second engine component for usage in at least one gas turbine engine corresponding to the at least one predicted response model.

    REVERSIBLE BLADE ROTOR SEAL WITH PROTRUSIONS
    12.
    发明申请
    REVERSIBLE BLADE ROTOR SEAL WITH PROTRUSIONS 有权
    可逆刀片转子密封件

    公开(公告)号：US20160376903A1

    公开(公告)日：2016-12-29

    申请号：US14748876

    申请日：2015-06-24

    Applicant: United Technologies Corporation

    Inventor： Christopher Corcoran ,  Daniel A. Snyder

    IPC: F01D11/00 ,  F02C7/18 ,  F16J15/02 ,  F01D5/08

    CPC classification number: F01D11/006 ,  F01D5/081 ,  F01D5/22 ,  F01D5/3015 ,  F01D11/008 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/55 ,  F05D2250/72 ,  F05D2260/20 ,  F16J15/02 ,  Y02T50/676

    Abstract: A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a first condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.

    Abstract translation: 用于燃气涡轮发动机的密封结构包括具有带槽的轮辋和冷却通道的转子。 转子可绕轴线转动。 第一和第二叶片布置在槽中并且分别包括在与冷却通道流体连通的凹穴内彼此面对的第一和第二搁架。 第一和第二个货架形成一个开口。 可口密封件布置在口袋内，并且具有构造成与四个取向中的任何一个中的第一和第二刀片操作关联的主体，以在第一状态下密封开口。 密封件包括分别从相对的第一和第二面延伸的第一和第二突起。 在第一状态下，第一凸起支撑在轮辋上。

    Low loss airfoil platform rim seal assembly
    13.
    发明授权
    Low loss airfoil platform rim seal assembly 有权

    公开(公告)号：US10648353B2

    公开(公告)日：2020-05-12

    申请号：US14942484

    申请日：2015-11-16

    Applicant: United Technologies Corporation

    Inventor： Andrew S. Aggarwala ,  Russell J. Bergman ,  Mark A. Boeke ,  Kyle C. Lana ,  Daniel A. Snyder

    IPC: F01D11/02 ,  F01D11/00 ,  F01D5/22

    Abstract: An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity.

    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS
    14.
    发明申请
    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS 审中-公开

    公开(公告)号：US20200012749A1

    公开(公告)日：2020-01-09

    申请号：US16026547

    申请日：2018-07-03

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder ,  David J. Yudichak ,  Kurt R. Heinemann ,  Perry Bowes ,  Evan Selin

    IPC: G06F17/50

    Abstract: A qualification system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters. The computer system includes at least one simulated engine model configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, a correlation system configured to correlate variations in the set of parameters for each of the gas turbine engine components with a set of the predicted operations of each gas turbine engine, thereby generating a predictive model based on the variations. The computer system also includes a qualification module configured to generate a qualification formula based on the predictive model. The qualification formula is configured to receive a set of measured parameters of an as-manufactured gas turbine engine component and determine when the as manufactured gas turbine engine component is qualified for inclusion in at least one engine.

    SEAL AND CLIP-ON DAMPER SYSTEM AND DEVICE
    20.
    发明申请
    SEAL AND CLIP-ON DAMPER SYSTEM AND DEVICE 有权
    密封和夹紧阻尼器系统和装置

    公开(公告)号：US20160194972A1

    公开(公告)日：2016-07-07

    申请号：US14852856

    申请日：2015-09-14

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder

    IPC: F01D11/00 ,  F01D5/10 ,  F16J15/06

    CPC classification number: F01D11/006 ,  F01D5/10 ,  F01D5/22 ,  F05D2220/32 ,  F05D2240/55 ,  F16J15/064

    Abstract: A seal and damper system is provided. The system comprises a blade assembly seal with a central portion defining a recess and a depression. The system also includes a damper comprising a center body and an arm extending from the center body and configured to engage the depression. A blade assembly is also provided comprising a blade platform, a seal configured to press against the blade platform, and a damper clipped onto the seal.

    Abstract translation: 提供密封和阻尼系统。 该系统包括具有限定凹部和凹陷部的中心部分的叶片组件密封件。 该系统还包括阻尼器，该阻尼器包括中心体和从中心体延伸并被构造成接合凹陷的臂。 还提供了一种刀片组件，其包括刀片平台，被配置为压靠刀片平台的密封件和夹在密封件上的阻尼器。

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