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    ENDWALL CONTOURING
    1.
    发明申请
    ENDWALL CONTOURING 审中-公开
    端到端

    公开(公告)号：WO2014074190A3

    公开(公告)日：2014-07-17

    申请号：PCT/US2013054944

    申请日：2013-08-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PRAISNER THOMAS J ,  AGGARWALA ANDREW S ,  NASH TIMOTHY CHARLES ,  ALLEN-BRADLEY EUNICE ,  GROVER ERIC A

    IPC: F01D1/04 ,  F01D5/02 ,  F01D5/22 ,  F04D29/44

    CPC classification number: F01D9/02 ,  F01D5/143 ,  F01D5/145 ,  F04D29/324 ,  F04D29/542 ,  F04D29/681 ,  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 adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said 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凸出的轮廓区域，该凸形轮廓区域从靠近所述多个翼型件中的至少一个的前缘的所述多个翼型件中的至少一个的第一侧面的端壁延伸，并且在所述多个翼型件中的凹形轮廓区域 并且延伸穿过所述多个流动通道中的所述至少一个。

    VARIABLE AREA VANE ENDWALL TREATMENTS
    2.
    发明申请
    VARIABLE AREA VANE ENDWALL TREATMENTS 审中-公开
    可变面积叶片端壁治疗

    公开(公告)号：WO2015099869A3

    公开(公告)日：2015-09-24

    申请号：PCT/US2014061333

    申请日：2014-10-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TEIXEIRA JOHN D ,  GROVER ERIC A ,  SURACE RAYMOND

    IPC: F01D9/02 ,  F01D17/16

    CPC classification number: F01D17/162 ,  F01D5/143 ,  F05D2250/241 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

    Abstract: A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap. The outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the body rotates about the axis.

    Abstract translation: 燃气涡轮发动机部件包括外径端壁，在外径端壁径向向内间隔开的内径端壁以及支撑在外端壁和内端壁之间用于围绕轴线旋转的至少一个主体。 所述主体包括外径表面，所述外径表面与所述外径端壁间隔开第一间隙和与所述内径端壁间隔第二间隙的内径表面。 外径和内径表面以及外径和内径端壁被构造成使得当主体围绕轴线旋转时第一和第二间隙的尺寸通常保持恒定。

    VARIABLE AREA TURBINE VANE ROW ASSEMBLY
    3.
    发明申请
    VARIABLE AREA TURBINE VANE ROW ASSEMBLY 审中-公开
    可变区涡轮风扇组件

    公开(公告)号：WO2015084452A3

    公开(公告)日：2015-08-20

    申请号：PCT/US2014055743

    申请日：2014-09-16

    Applicant: UNITED TECHNOLOGIES CORP ,  GROVER ERIC A

    Inventor： GROVER ERIC A

    IPC: F01D17/16 ,  F01D9/02 ,  F02K3/06

    CPC classification number: F01D17/162 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2250/73 ,  F05D2260/961

    Abstract: The present disclosure relates generally to a variable area turbine vane row assembly. In an embodiment, the variable area turbine vane row assembly includes rotatable vanes that are circumferentially biased and/or axially biased with respect to adjacent fixed vanes. In another embodiment, the variable area turbine vane row assembly includes multiple rotatable vanes positioned between adjacent fixed vanes, which may optionally be circumferentially biased and/or axially biased with respect to each other as well as to the adjacent fixed vanes.

    Abstract translation: 本公开一般涉及可变区域涡轮叶片排组件。 在一个实施例中，可变区域涡轮叶片排组件包括相对于相邻固定叶片周向地偏置和/或轴向偏置的可旋转叶片。 在另一个实施例中，可变区域涡轮叶片排组件包括位于相邻的固定叶片之间的多个可旋转叶片，其可任选地相对于彼此以及相邻的固定叶片周向地偏置和/或轴向偏置。

    ENDWALL CONTOURING
    4.
    发明申请
    ENDWALL CONTOURING 审中-公开

    公开(公告)号：WO2014070279A3

    公开(公告)日：2014-07-10

    申请号：PCT/US2013054949

    申请日：2013-08-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： AGGARWALA ANDREW S ,  GROVER ERIC A

    IPC: F01D1/04 ,  F01D5/02 ,  F01D5/22 ,  F04D29/44

    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，以及从端壁径向突出的多个翼型件。 每个翼型可以具有在前缘和后缘之间沿弦轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上沿圆周间隔开，从而在相邻翼型件之间限定多个流动通道。 翼型阵列可进一步包括从靠近所述多个翼型件中的至少一个的前缘的端壁和靠近所述多个流动通道中的至少一个的中间的端壁中的凹形轮廓区域延伸的凸形轮廓区域。

    ENDWALL CONTOURING
    5.
    发明申请
    ENDWALL CONTOURING 审中-公开
    端到端

    公开(公告)号：WO2014070280A3

    公开(公告)日：2014-06-26

    申请号：PCT/US2013054953

    申请日：2013-08-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PRAISNER THOMAS J ,  AGGARWALA ANDREW S ,  GROVER ERIC A ,  JUREK RENEE J

    IPC: F01D1/04 ,  F01D5/02 ,  F01D5/22 ,  F04D29/44

    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沿弦向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。 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凸形轮廓区域的后端的端壁中的凹形轮廓区域。

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