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    TURBINE BLADE DAMPER SEAL
    1.
    发明申请
    TURBINE BLADE DAMPER SEAL 审中-公开
    涡轮叶片减振器密封

    公开(公告)号：WO2013154657A2

    公开(公告)日：2013-10-17

    申请号：PCT/US2013/023132

    申请日：2013-01-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SNYDER, Daniel A. ,  LANA, Kyle, Charles ,  SANDOVAL, Jonathan, Perry ,  VIRKLER, Scott, Daniel ,  TARASKEVICH, Jaimie ,  OTERO, Edwin

    IPC: F01D11/00 ,  F01D5/14

    CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

    Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

    Abstract translation: 根据本公开的一个示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮叶片的空腔中的阻尼密封件包括中间主体部分，其具有 第一端部区域，相对的第二端部区域和宽度。 阻尼器密封件还包括从中央主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突片，该第一向外延伸的突片限定了第一扩大部分，该第一扩大部分具有大于 中央主体部分和从中央主体部分的相对的第二端部区域延伸的第二部分。

    GAS TURBINE ENGINE DAMPING DEVICE
    4.
    发明公开
    GAS TURBINE ENGINE DAMPING DEVICE 有权
    GASTURBINENMOTORDÄMPFUNGSVORRICHTUNG

    公开(公告)号：EP3088676A1

    公开(公告)日：2016-11-02

    申请号：EP16164198.0

    申请日：2016-04-07

    Applicant: United Technologies Corporation

    Inventor： SNYDER, Daniel A.

    IPC: F01D5/24 ,  F01D5/22

    Abstract: A gas turbine engine assembly includes a damping device (100) having a first side (104) and a second side (108) facing away from the first side (104). The first side (104) is configured to hold a seal (102) when the second side (108) engages an extension (90) from a gas turbine engine component (76). The first side (104) is further configured to engage the extension (90) when the second side (108) holds the seal (102).

    Abstract translation: 燃气涡轮发动机组件包括具有第一侧面（104）和背离第一侧面（104）的第二侧面（108）的阻尼装置（100）。 当第二侧（108）与燃气涡轮发动机部件（76）接合延伸部（90）时，第一侧（104）构造成保持密封件（102）。 当第二侧（108）保持密封件（102）时，第一侧（104）进一步构造成与延伸部（90）接合。

    TURBINE BLADE DAMPER SEAL
    6.
    发明公开
    TURBINE BLADE DAMPER SEAL 审中-公开
    用缓冲密封件的涡轮叶片

    公开(公告)号：EP2836682A2

    公开(公告)日：2015-02-18

    申请号：EP13775907.2

    申请日：2013-01-25

    Applicant: United Technologies Corporation

    Inventor： SNYDER, Daniel A. ,  LANA, Kyle, Charles ,  SANDOVAL, Jonathan, Perry ,  VIRKLER, Scott, Daniel ,  TARASKEVICH, Jaimie ,  OTERO, Edwin

    IPC: F01D5/26

    CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

    Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS FOR TARGET BASED INVENTORY QUALIFICATION
    8.
    发明公开
    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS FOR TARGET BASED INVENTORY QUALIFICATION 审中-公开

    公开(公告)号：EP3591173A1

    公开(公告)日：2020-01-08

    申请号：EP19183986.9

    申请日：2019-07-02

    Applicant: United Technologies Corporation

    Inventor： SNYDER, Daniel A. ,  HEINEMANN, Kurt R.

    IPC: F01D21/00 ,  F01D25/00 ,  F02C9/00 ,  G01M15/14

    Abstract: An exemplary method for qualifying a gas turbine engine component (174) includes creating a first set of substantially identical gas turbine engine components (174) via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component (174) in the first set of substantially identical gas turbine engine components (174), determining a variance model of the first set of substantially identical gas turbine engine components (174), 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 (174) from the first set of substantially identical gas turbine engine components (174) in the corresponding one of the engine type and the engine assembly.
    The system then identifies as-manufactured parameters of a second engine component (174), and applies the as-manufactured parameters of the second engine component (174) 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 (174).

    REVERSIBLE BLADE ROTOR SEAL WITH PROTRUSIONS
    9.
    发明公开
    REVERSIBLE BLADE ROTOR SEAL WITH PROTRUSIONS 审中-公开
    UMKEHRBARE SCHAUFELROTORDICHTUNG MITVORSPRÜNGEN

    公开(公告)号：EP3109403A1

    公开(公告)日：2016-12-28

    申请号：EP16176255.4

    申请日：2016-06-24

    Applicant: United Technologies Corporation

    Inventor： CORCORAN, Christopher ,  SNYDER, Daniel A.

    IPC: F01D5/08 ,  F01D5/22 ,  F01D5/30 ,  F01D11/00

    Abstract: A sealing structure for a gas turbine engine (20) includes a rotor (62) that has a rim (63) with slots (69) and a cooling passage (65). The rotor (62) is rotatable about an axis (A). First and second blades (64) are arranged in the slots (69) and respectively including first and second shelves (72) facing one another within a pocket (74) that is in fluid communication with the cooling passage (65). The first and second shelves (72) form an opening (77). A reversible seal (80) is arranged within the pocket (74) and has a body that is configured for operative association with the first and second blades (64) in any of four orientations to seal the opening (77) in a first condition. The seal includes first and second protrusions (96, 98) respectively extending from first and second faces opposing one another. The first protrusions (96, 98) supported on the rim (63) in a first condition.

    Abstract translation: 用于燃气涡轮发动机（20）的密封结构包括具有带槽（69）和冷却通道（65）的轮辋（63）的转子（62）。 转子（62）能够围绕轴线（A）旋转。 第一和第二叶片（64）布置在槽（69）中并且分别包括在与冷却通道（65）流体连通的凹穴（74）内彼此面对的第一和第二搁架（72）。 第一和第二搁架（72）形成开口（77）。 可逆密封件（80）布置在凹穴（74）内并且具有构造成在四个取向中的任何一个中与第一和第二叶片（64）可操作地关联的主体，以在第一状态下密封开口（77）。 密封件包括分别从彼此相对的第一和第二面延伸的第一和第二突起（96,98）。 第一突起（96,98）在第一状态下支撑在轮辋（63）上。

    COMPONENTS AND CORRESPONDING METHOD FOR PRODUCING
    10.
    发明公开
    COMPONENTS AND CORRESPONDING METHOD FOR PRODUCING 审中-公开
    生产零件的组件和相应的方法

    公开(公告)号：EP3170980A1

    公开(公告)日：2017-05-24

    申请号：EP16199685.5

    申请日：2016-11-18

    Applicant: United Technologies Corporation

    Inventor： SNYDER, Daniel A. ,  PROPHETER-HINCKLEY, Tracy A. ,  MONGILLO, Dominic J.

    IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08

    CPC classification number: F01D5/187 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/204 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A component (60) according to the present disclosure includes a wall (84) and a hollow or solid vascular engineered lattice structure (80; 280; 380; 480A; 480B) formed inside of the wall (84). The vascular engineered lattice structure (80...480B) has an inlet hole (288) and an outlet hole (90; 290) that communicate fluid (68) into and out of the vascular structure (80...480B). The vascular engineered lattice structure (80...480B) further has at least one resupply inlet hole (88A; 88B) between the inlet hole (288) and the outlet hole (90; 290) to communicate additional fluid (68) into the vascular engineered lattice structure (80...480B).

    Abstract translation: 根据本公开的部件（60）包括形成在壁（84）内部的壁（84）和空心或实心的血管工程格子结构（80; 280; 380; 480A; 480B）。 血管工程晶格结构（80 ... 480B）具有将流体（68）连通到血管结构（80 ... 480B）和从血管结构（80 ... 480B）流出的入口孔（288）和出口孔（90; 290）。 血管工程格栅结构（80 ... 480B）还在入口孔（288）和出口孔（90; 290）之间具有至少一个补给入口孔（88A; 88B），以将附加流体（68） 血管工程晶格结构（80 ... 480B）。

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