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    Gas turbine engine with dove-tailed TOBI vane
    13.
    发明授权
    Gas turbine engine with dove-tailed TOBI vane 有权

    公开(公告)号：US11092025B2

    公开(公告)日：2021-08-17

    申请号：US16668773

    申请日：2019-10-30

    Applicant: United Technologies Corporation

    Inventor： Meggan Harris

    IPC: F01D9/06 ,  F01D9/04 ,  F01D5/08 ,  F01D25/12 ,  F01D5/30

    Abstract: A combustor assembly for a gas turbine engine includes a TOBI module that includes a TOBI housing. The TOBI housing has a slot. A vane includes a dovetail removably received within the slot. The TOBI housing includes an axially extending TOBI nozzle array. The TOBI housing includes a plenum. A cooling passage fluidly connects the plenum to the vane. The TOBI housing includes passages configured to provide cooling fluid to the vane. The TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum.

    Structural honeycomb panel
    14.
    发明授权
    Structural honeycomb panel 有权

    公开(公告)号：US10337339B2

    公开(公告)日：2019-07-02

    申请号：US15028129

    申请日：2014-12-09

    Applicant: United Technologies Corporation

    Inventor： Meggan Harris

    IPC: B32B3/30 ,  F01D9/02 ,  F01D25/12 ,  F01D25/24 ,  B22F3/105 ,  B22F5/10 ,  F02C7/24 ,  F02K1/82 ,  B22F5/00 ,  B33Y10/00 ,  B33Y80/00

    Abstract: A structural panel for use with a gas turbine engine includes a first exterior wall, a second exterior wall, and interior walls. The first exterior wall includes a first exterior surface and a first interior surface parallel to the first exterior surface. The second exterior wall includes a second exterior surface and a second interior surface parallel to the second exterior surface. The interior walls extend from the first interior surface to the second interior surface. The interior walls are arranged to form a pattern of hexagonal cells. The pattern of hexagonal cells includes cell groups having a variation in structural strength such that at least one of the cell groups has a structural strength that is not the same as the remaining cell groups.

    DIVERGENT FLAP
    15.
    发明申请
    DIVERGENT FLAP 审中-公开

    公开(公告)号：US20160237948A1

    公开(公告)日：2016-08-18

    申请号：US15028141

    申请日：2015-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Meggan Harris

    IPC: F02K1/12

    Abstract: A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The first wall and the second wall each extend from the hinge joint to the plow end. The second wall is spaced apart from the first wall by the two side walls to form at least one cooling channel extending between the hinge joint and the plow end. The divergent flap is integrally formed in layer-by-layer fashion as a single piece.

    Abstract translation: 发散片包括铰链接头，用于将发散片连接到收敛片，犁结构，第一壁，第二壁和两个侧壁。 犁式结构位于翼片的与铰链接头相对的犁端。 第一壁和第二壁各自从铰链接头延伸到犁端。 第二壁通过两个侧壁与第一壁间隔开，以形成在铰链接头和犁端之间延伸的至少一个冷却通道。 发散片整体形成为一体的单层。

    Swirler mount interface for gas turbine engine combustor
    17.
    发明授权
    Swirler mount interface for gas turbine engine combustor 有权

    公开(公告)号：US10598381B2

    公开(公告)日：2020-03-24

    申请号：US14904872

    申请日：2014-05-15

    Applicant: United Technologies Corporation

    Inventor： Christopher Drake ,  Seth A. Max ,  Meggan Harris

    IPC: F23R3/14 ,  F23R3/28

    Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.

    GAS TURBINE ENGINE WITH DOVE-TAILED TOBI VANE
    18.
    发明申请
    GAS TURBINE ENGINE WITH DOVE-TAILED TOBI VANE 审中-公开

    公开(公告)号：US20200063582A1

    公开(公告)日：2020-02-27

    申请号：US16668773

    申请日：2019-10-30

    Applicant: United Technologies Corporation

    Inventor： Meggan Harris

    IPC: F01D9/06 ,  F01D9/04 ,  F01D5/08 ,  F01D25/12

    Abstract: A combustor assembly for a gas turbine engine includes a TOBI module that includes a TOBI housing. The TOBI housing has a slot. A vane includes a dovetail removably received within the slot. The TOBI housing includes an axially extending TOBI nozzle array. The TOBI housing includes a plenum. A cooling passage fluidly connects the plenum to the vane. The TOBI housing includes passages configured to provide cooling fluid to the vane. The TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum.

    Divergent flap
    19.
    发明授权
    Divergent flap 有权

    公开(公告)号：US10519897B2

    公开(公告)日：2019-12-31

    申请号：US15028141

    申请日：2015-01-21

    Applicant: United Technologies Corporation

    Inventor： Meggan Harris

    IPC: F02K1/12 ,  F02K1/82 ,  F02K9/97 ,  B64D33/04

    Abstract: A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The first wall and the second wall each extend from the hinge joint to the plow end. The second wall is spaced apart from the first wall by the two side walls to form at least one cooling channel extending between the hinge joint and the plow end. The divergent flap is integrally formed in layer-by-layer fashion as a single piece.

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