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    Aircraft component qualification system and process for target based inventory qualification
    22.
    发明授权
    Aircraft component qualification system and process for target based inventory qualification 有权

    公开(公告)号：US11281821B2

    公开(公告)日：2022-03-22

    申请号：US16026586

    申请日：2018-07-03

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder ,  Kurt R. Heinemann

    IPC: G06F30/20 ,  G06F111/10 ,  G06N20/00

    Abstract: An exemplary 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 of substantially identical gas turbine engine components, determining a variance model of the first set of substantially identical gas turbine engine components, and determining a plurality of predicted response models based at least in part on the variance model, each of the predicted response models corresponding to one of an engine type and an engine assembly, and each of the predicted response models being configured to determine a predicted response of including a gas turbine engine component from the first set of substantially identical gas turbine engine components in the corresponding one of the engine type and the engine assembly. The system then identifies as-manufactured parameters of a second engine component, and applies the as-manufactured parameters of the second engine component to each of the predicted response models, thereby generating a predicted response output from each of the predicted response models. An optimum predicted response from each of the generated predicted response models is identified and the engine type or engine assembly that corresponds with the optimum predicted response is associated with a unique part identifier of the second engine component.

    Turbomachine blade
    23.
    发明授权
    Turbomachine blade 有权

    公开(公告)号：US11261737B1

    公开(公告)日：2022-03-01

    申请号：US15871260

    申请日：2018-01-15

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder ,  Edwin Otero ,  Di Wu ,  Timothy Charles Nash ,  Brandon W. Spangler

    IPC: F01D5/28 ,  F01D5/16 ,  F01D5/14 ,  F01D5/18

    Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858±10% Hz; a second mode resonance frequency is 4916±10% Hz; a third mode resonance frequency is 7160±10% Hz; a fourth mode resonance frequency is 10268±10% Hz; a fifth mode resonance frequency is 14235±10% Hz; and a sixth mode resonance frequency is 15088±10% Hz.

    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS FOR TARGET BASED INVENTORY QUALIFICATION
    24.
    发明申请
    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS FOR TARGET BASED INVENTORY QUALIFICATION 审中-公开

    公开(公告)号：US20200012750A1

    公开(公告)日：2020-01-09

    申请号：US16026586

    申请日：2018-07-03

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder ,  Kurt R. Heinemann

    IPC: G06F17/50

    Abstract: An exemplary 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 of substantially identical gas turbine engine components, determining a variance model of the first set of substantially identical gas turbine engine components, and determining a plurality of predicted response models based at least in part on the variance model, each of the predicted response models corresponding to one of an engine type and an engine assembly, and each of the predicted response models being configured to determine a predicted response of including a gas turbine engine component from the first set of substantially identical gas turbine engine components in the corresponding one of the engine type and the engine assembly.The system then identifies as-manufactured parameters of a second engine component, and applies the as-manufactured parameters of the second engine component to each of the predicted response models, thereby generating a predicted response output from each of the predicted response models. An optimum predicted response from each of the generated predicted response models is identified and the engine type or engine assembly that corresponds with the optimum predicted response is associated with a unique part identifier of the second engine component.

    AIRFOIL SUPPORT AND COOLING SCHEME
    28.
    发明申请
    AIRFOIL SUPPORT AND COOLING SCHEME 有权
    气翼支撑和冷却方案

    公开(公告)号：US20160215628A1

    公开(公告)日：2016-07-28

    申请号：US14605366

    申请日：2015-01-26

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Edwin Otero ,  Daniel A. Snyder ,  Jaimie Taraskevich ,  Di Wu

    IPC: F01D5/18 ,  F02C3/04 ,  F02C7/18 ,  F01D5/14

    CPC classification number: F01D5/187 ,  F01D5/147 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.

    Abstract translation: 在各种实施例中，提供了用作燃气涡轮发动机中的涡轮机叶轮的涡轮叶片的翼型件。 翼型件可以包括根部，尖端和主体。 根可能有第一个区域。 尖端可以具有第二区域。 身体可能有一个由根和尖端限定的和弦。 主体还可以限定冷却室。 冷却室可以具有基本上垂直于弦的第一肋。 冷却室还可以具有部分地在根部和尖端之间延伸的第二肋条。

    LOW LOSS AIRFOIL PLATFORM RIM SEAL ASSEMBLY
    29.
    发明申请
    LOW LOSS AIRFOIL PLATFORM RIM SEAL ASSEMBLY 审中-公开
    低损失空气平台RIM密封组件

    公开(公告)号：US20160153304A1

    公开(公告)日：2016-06-02

    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: F01D11/00 ,  F01D5/22

    CPC classification number: F01D11/006 ,  F01D5/22 ,  F01D11/001 ,  F01D11/02

    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.

    Abstract translation: 涡轮发动机的翼型段包括上游翼型组件，与上游翼型组件成旋转关系的下游翼型组件和集成在其间的边缘密封组件。 轮辋密封组件可以包括上游翼型组件的平台的倾斜下游部分，下游翼型组件的平台的上游部分和从上游部分径向向外突出的凸块。 下游部分和上游段彼此间隔开，在其间限定冷却空气的流动。 该部分和部分轴向重叠，使得该凸块与下游部分轴向对齐，以改善冷却效果并减少进入冷却腔的芯气流。

    REVERSIBLE BLADE ROTOR SEAL
    30.
    发明申请
    REVERSIBLE BLADE ROTOR SEAL 审中-公开
    可逆叶片转子密封

    公开(公告)号：US20160032751A1

    公开(公告)日：2016-02-04

    申请号：US14804894

    申请日：2015-07-21

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder

    IPC: F01D11/00 ,  F01D5/30 ,  F01D5/12

    CPC classification number: F01D11/006 ,  F01D5/12 ,  F01D5/22 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2250/22 ,  F16J15/0887

    Abstract: A rotatable sealing structure for a gas turbine engine includes a first blade and a second blade. A seal is arranged between the blades and has a body that is configured for operative association with the first and second blades in a first orientation and in a second orientation to seal a gap defined between the blades.

    Abstract translation: 用于燃气涡轮发动机的可旋转密封结构包括第一叶片和第二叶片。 密封件布置在叶片之间并且具有构造成在第一方位和第二方向上与第一和第二叶片可操作地相关联的主体，以密封限定在叶片之间的间隙。

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