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    Endwall contouring
    11.
    发明授权
    Endwall contouring 有权
    端壁轮廓

    公开(公告)号：US09212558B2

    公开(公告)日：2015-12-15

    申请号：US13663977

    申请日：2012-10-30

    Applicant: United Technologies Corporation

    Inventor： Thomas J. Praisner ,  Andrew S. Aggarwala ,  Eric A. Grover ,  Renee J. Jurek

    IPC: F01D9/00 ,  F02C3/04 ,  F01D5/14

    CPC classification number: F01D5/145 ,  F01D5/143 ,  F04D29/324 ,  F04D29/329 ,  F04D29/547 ,  F04D29/681 ,  F05D2240/123 ,  F05D2240/305 ,  F05D2250/712 ,  Y02T50/673

    Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.

    Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型阵列还可以包括从邻近所述多个翼型中的至少一个翼型件的第一侧的端壁延伸并且在所述多个翼型中的至少一个翼型件的前缘附近的凸形轮廓区域。 所述翼型阵列还可包括邻近所述多个翼型件中的所述至少一个翼型件的第一侧和所述凸形轮廓区域的后部的所述端壁中的凹形轮廓区域。

    Low loss airfoil platform rim seal assembly
    12.
    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.

    Vane assembly of a gas turbine engine
    13.
    发明授权
    Vane assembly of a gas turbine engine 有权

    公开(公告)号：US10287901B2

    公开(公告)日：2019-05-14

    申请号：US14938484

    申请日：2015-11-11

    Applicant: United Technologies Corporation

    Inventor： Andrew S. Aggarwala

    IPC: F01D9/04 ,  F01D5/02 ,  F01D15/12 ,  F01D25/24 ,  F01D5/14

    Abstract: A first stage vane array of a high pressure turbine that may be for a geared turbofan engine includes a plurality of airfoils circumferentially spaced from one-another and orientated about an engine axis. Each airfoil has a leading edge and a trailing edge with the trailing edge being circumferentially separated by the next adjacent trailing edge by a pitch distance. The leading a trailing edges of each one of the plurality of airfoils are axially separated by an axial chord length. A pitch-to-chord ratio of the pitch distance over the axial chord length is equal to or greater than 1.7.

    TIP LEAKAGE FLOW DIRECTIONALITY CONTROL
    15.
    发明申请
    TIP LEAKAGE FLOW DIRECTIONALITY CONTROL 审中-公开

    公开(公告)号：US20180202297A1

    公开(公告)日：2018-07-19

    申请号：US15918190

    申请日：2018-03-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark F. Zelesky ,  Andrew S. Aggarwala

    IPC: F01D5/18 ,  F01D11/10 ,  F01D5/14 ,  F01D5/20

    CPC classification number: F01D5/187 ,  F01D5/146 ,  F01D5/18 ,  F01D5/186 ,  F01D5/20 ,  F01D11/10 ,  F05D2240/307 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil according to an example includes, among other things, a suction sidewall and a pressure sidewall. A tip wall extends from a leading edge to a trailing edge and joins respective outer ends of the suction and pressure sidewalls. A tip rib extends along a pressure side of the tip wall. A tip leakage control channel is provided at the tip wall and has a floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. Each of the tip leakage control vanes is contiguous with and extending from a suction side surface of the tip rib. The tip leakage channel extends toward the trailing edge while extending toward the suction sidewall. One or more of an internal cavity, a channel cooling aperture, and a sidewall microcircuit may be provided.

    Endwall contouring
    18.
    发明授权
    Endwall contouring 有权
    端壁轮廓

    公开(公告)号：US09140128B2

    公开(公告)日：2015-09-22

    申请号：US13663894

    申请日：2012-10-30

    Applicant: United Technologies Corporation

    Inventor： Andrew S. Aggarwala ,  Eric A. Grover

    IPC: F02C3/04 ,  F01D5/02 ,  F01D9/04 ,  F01D5/14

    CPC classification number: F01D5/143 ,  F04D29/321 ,  F04D29/681 ,  F05D2240/303 ,  F05D2240/80 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

    Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall near the leading edge of at least one of said plurality of airfoils, and a concave profiled region in the endwall near a middle of at least one of said plurality of flow passages.

    Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上周向间隔开，从而在相邻翼型之间限定多个流动通道。 翼型阵列还可以包括从所述多个翼型件中的至少一个翼型件的前缘附近的端壁延伸的凸形轮廓区域，以及在所述多个流动通道中的至少一个流动通道的中间附近的端壁中的凹形轮廓区域。

    Endwall Controuring
    19.
    发明申请
    Endwall Controuring 有权
    端壁控制

    公开(公告)号：US20140090401A1

    公开(公告)日：2014-04-03

    申请号：US13663977

    申请日：2012-10-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Thomas J. Praisner ,  Andrew S. Aggarwala ,  Eric A. Grover ,  Renee J. Jurek

    IPC: F01D9/00 ,  F02C3/04

    CPC classification number: F01D5/145 ,  F01D5/143 ,  F04D29/324 ,  F04D29/329 ,  F04D29/547 ,  F04D29/681 ,  F05D2240/123 ,  F05D2240/305 ,  F05D2250/712 ,  Y02T50/673

    Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.

    Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型阵列还可以包括从邻近所述多个翼型中的至少一个翼型件的第一侧的端壁延伸并且在所述多个翼型中的至少一个翼型件的前缘附近的凸形轮廓区域。 所述翼型阵列还可包括邻近所述多个翼型件中的所述至少一个翼型件的第一侧和所述凸形轮廓区域的后部的所述端壁中的凹形轮廓区域。

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