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    GAS TURBINE ENGINE AIRFOIL SQUEALER POCKET COOLING HOLE CONFIGURATION
    61.
    发明申请
    GAS TURBINE ENGINE AIRFOIL SQUEALER POCKET COOLING HOLE CONFIGURATION 审中-公开
    气体涡轮发动机空气调节器口袋冷却孔配置

    公开(公告)号：US20170002663A1

    公开(公告)日：2017-01-05

    申请号：US14790231

    申请日：2015-07-02

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Scott D. Lewis ,  Steven Bruce Gautschi ,  Christopher King ,  Christopher Corcoran ,  David Donald Chapdelaine

    IPC: F01D5/18

    CPC classification number: F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.

    Abstract translation: 燃气涡轮发动机翼型件包括提供沿径向方向延伸到尖端的外部翼面表面的主体。 外表面具有向前方向的前缘和向后方的后缘。 尖端包括具有凹陷表面的尖叫口袋。 冷却通道设置在体内。 每个冷却孔从冷却通道的入口延伸到凹陷表面处的出口。 入口和出口相对于凹入表面以角度方向成一定角度布置。 角度方向朝着前后方向中的至少一个方向。

    Turbine airfoil tip shelf and squealer pocket cooling
    63.
    发明授权
    Turbine airfoil tip shelf and squealer pocket cooling 有权
    涡轮机翼尖架和尖叫口袋冷却

    公开(公告)号：US09429027B2

    公开(公告)日：2016-08-30

    申请号：US14748666

    申请日：2015-06-24

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo, Jr. ,  Steven Bruce Gautschi ,  San Quach

    IPC: F01D5/08 ,  F01D5/20

    CPC classification number: F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil includes a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil. The airfoil also includes a leading edge and a trailing edge defining a chord length of the airfoil therebetween. The airfoil further includes a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall. The tip shelf wall is spaced between the pressure surface and the suction surface and the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.

    Abstract translation: 翼型件包括压力表面和从翼型件的根部部分延伸到翼型件的尖端部分的抽吸表面。 翼型件还包括前缘和后缘，其在它们之间限定翼型的翼弦长度。 所述翼型件还包括沿所述翼型件的所述尖端部分在所述压力表面和尖端搁板壁之间形成的尖端架。 尖端架壁在压力表面和吸力表面之间间隔开，并且尖端架从从前缘测量的弦长的10％范围内延伸到从后缘测量的弦长的10％以内。

    PEDESTALS WITH HEAT TRANSFER AUGMENTER
    64.
    发明申请
    PEDESTALS WITH HEAT TRANSFER AUGMENTER 审中-公开
    带有传热装置的底盘

    公开(公告)号：US20160230664A1

    公开(公告)日：2016-08-11

    申请号：US15023010

    申请日：2014-10-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： San Quach ,  Thomas N. Slavens

    IPC: F02C7/18 ,  F01D25/12

    CPC classification number: F02C7/18 ,  F01D5/187 ,  F01D25/12 ,  F05D2250/181 ,  F05D2250/20 ,  F05D2250/23 ,  F05D2250/25 ,  F05D2250/281 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

    Abstract translation: 燃气涡轮发动机部件包括第一侧壁和与第一侧壁间隔开的第二侧壁。 在第一和第二侧壁之间形成至少一个内部冷却通道。 至少一个基座定位在至少一个冷却通道内，并且具有从连接到第一侧壁的第一端延伸到连接到第二侧壁的第二端的主体。 主体包括至少一个突起。

    Turbine Airfoil Cooling Core Exit
    65.
    发明申请
    Turbine Airfoil Cooling Core Exit 审中-公开
    涡轮机翼冷却核心出口

    公开(公告)号：US20160222795A1

    公开(公告)日：2016-08-04

    申请号：US15022356

    申请日：2014-09-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： San Quach ,  Thomas N. Slavens

    IPC: F01D5/18 ,  B22C9/24 ,  B22C9/10

    CPC classification number: F01D5/187 ,  B22C9/00 ,  B22C9/10 ,  B22C9/24 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2230/50 ,  F05D2240/305 ,  F05D2240/307 ,  F05D2260/20 ,  Y02T50/676

    Abstract: A gas turbine engine component has an airfoil extending from a platform to a tip at an end of the airfoil spaced from the platform. The airfoil has a suction wall and a pressure wall, with at least one channel extending toward the tip from the platform. A plenum communicates with the at least one channel. The plenum flows from the suction wall toward the pressure wall at the tip to communicate with cooling holes near the pressure wall. The plenum has a reduced cross-sectional area between the suction wall and the pressure wall, and an increase in cross-sectional area downstream of the reduced cross-sectional area. A mold core is also disclosed.

    Abstract translation: 燃气涡轮发动机部件具有从平台延伸到在与平台间隔开的翼型的端部处的尖端的翼型件。 翼型件具有吸力壁和压力壁，至少一个通道从平台向尖端延伸。 一个通风室与至少一个通道通信。 气室从吸力壁向尖端的压力壁流动，以与靠近压力壁的冷却孔相通。 增压室在吸壁和压壁之间具有减小的横截面积，并且在减小的横截面积的下游的横截面面积增加。 还公开了一种模芯。

    GAS TURBINE ENGINE TURBINE BLADE LEADING EDGE TIP TRENCH COOLING
    67.
    发明申请
    GAS TURBINE ENGINE TURBINE BLADE LEADING EDGE TIP TRENCH COOLING 审中-公开
    气体涡轮发动机涡轮叶片前沿叶片倾斜冷却

    公开(公告)号：US20140165593A1

    公开(公告)日：2014-06-19

    申请号：US13713371

    申请日：2012-12-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： San Quach ,  Lane Thornton

    IPC: F01D5/12

    CPC classification number: F01D5/186 ,  F01D5/20 ,  F05D2240/303 ,  F05D2240/307 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A tip trench is provided in the tip and wrapping at least a portion of the airfoil from the pressure side wall around the leading edge to the suction side wall. The tip trench is provided by a recess.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端沟槽设置在尖端中，并且将翼型件的至少一部分从前缘的压力侧壁包裹到吸力侧壁。 尖端沟槽由凹槽提供。

    Mateface for blade outer air seals in a gas turbine engine
    68.
    发明授权
    Mateface for blade outer air seals in a gas turbine engine 有权

    公开(公告)号：US11384654B2

    公开(公告)日：2022-07-12

    申请号：US16686540

    申请日：2019-11-18

    Applicant: United Technologies Corporation

    Inventor： Winston Gregory Smiddy ,  San Quach ,  Matthew D. Parekh ,  Jeffrey T. Morton

    IPC: F01D11/10 ,  F01D25/14

    Abstract: A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.

    Baffle with tail
    69.
    发明授权
    Baffle with tail 有权

    公开(公告)号：US11280201B2

    公开(公告)日：2022-03-22

    申请号：US16600875

    申请日：2019-10-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Adam P. Generale ,  Lucas Dvorozniak ,  San Quach ,  Bryan P. Dube

    IPC: F01D5/18

    Abstract: An airfoil vane includes an airfoil section including an outer wall that defines an internal cavity; and a baffle situated in the internal cavity, the baffle including a baffle wall that defines a central cavity having a leading end and a trailing end corresponding to a leading end and a trailing end of the airfoil section, and a tail extending from the baffle wall, the tail including at least one feature configured to disturb an airflow surrounding the tail. A baffle for the airfoil vane assembly and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

    Impingement cooling arrangement for airfoils
    70.
    发明授权
    Impingement cooling arrangement for airfoils 有权

    公开(公告)号：US11255197B2

    公开(公告)日：2022-02-22

    申请号：US16734464

    申请日：2020-01-06

    Applicant: United Technologies Corporation

    Inventor： Jason Shenny ,  Jeffrey T. Morton ,  Alberto A. Mateo ,  San Quach ,  Gregory Anselmi

    IPC: F01D5/18 ,  F04D29/32 ,  F04D29/58

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

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