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    Turbine engine shroud assembly including axially floating shroud segment
    1.
    发明授权
    Turbine engine shroud assembly including axially floating shroud segment 有权
    涡轮发动机罩组件包括轴向浮动的护罩段

    公开(公告)号：US06884026B2

    公开(公告)日：2005-04-26

    申请号：US10260478

    申请日：2002-09-30

    申请人： Christopher Charles Glynn ,  Mary Ellen Alford ,  Mark Eugene Noe ,  Toby George Darkins, Jr.

    发明人： Christopher Charles Glynn ,  Mary Ellen Alford ,  Mark Eugene Noe ,  Toby George Darkins, Jr.

    IPC分类号： F01D11/08 ,  F02C7/20 ,  F04D29/08 ,  F04D29/44

    CPC分类号： F01D11/08 ,  F02C7/20 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2250/41 ,  F05D2300/603

    摘要： At least one shroud segment, floating axially independently of adjacent turbine engine shroud assembly members, includes a segment body comprising a radially outer surface and a radially outwardly projecting segment support that includes an axial support wall surface therein. The assembly includes a shroud hanger in axial juxtaposition with the segment support, and at least one axial support projection from the shroud hanger into the segment support at the support wall surface. The support projection supports the shroud segment releasably at the support wall surface sufficiently to enable relative axial movement of the shroud segment on the support projection independently of the shroud hanger and adjacent engine members.

    摘要翻译： 至少一个护罩段，其轴向独立于相邻的涡轮发动机罩组件构件浮动，包括一段，其包括径向外表面和径向向外突出的段支撑件，其包括其中的轴向支撑壁表面。 组件包括与分段支撑件轴向并置的护罩悬挂器，以及从护罩悬挂到支撑壁表面处的段支撑件中的至少一个轴向支撑突起。 支撑突出部可释放地支撑在支撑壁表面处的护罩区段，足以使护罩段在支撑突起上的相对轴向运动独立于护罩悬挂器和相邻的发动机构件。

    Turbine shroud segment and shroud assembly
    2.
    发明授权
    Turbine shroud segment and shroud assembly 有权
    涡轮护罩段和护罩组件

    公开(公告)号：US06702550B2

    公开(公告)日：2004-03-09

    申请号：US10050451

    申请日：2002-01-16

    申请人： Toby George Darkins, Jr. ,  Mary Ellen Alford ,  Christopher Charles Glynn

    发明人： Toby George Darkins, Jr. ,  Mary Ellen Alford ,  Christopher Charles Glynn

    IPC分类号： F01D1108

    CPC分类号： F01D11/08 ,  F01D9/04 ,  F01D11/24 ,  F01D25/12

    摘要： A turbine engine shroud segment, preferably a low ductility material, for example a ceramic matrix composite, comprises a segment body extending between body circumferential ends. The body includes a body radially inner surface arcuate at least circumferentially, and a body radially outer surface from which a plurality of hooks extend generally radially outwardly. Each hook comprises a generally radially outwardly extending hook arm with a generally axially extending hook end having a generally radially inner surface in spaced apart juxtaposition with a portion of the body radially outer surface. Such body outer surface includes at least two body contact surfaces each matched in shape and in juxtaposition at least at body circumferential ends with a cooperating hanger contact surface. The radially inner surface of each hook end includes a hook end contact surface matched in shape with a cooperating hanger contact surface at least in a circumferential middle portion of such surface. In a turbine engine shroud assembly, a plurality of such shroud segments are assembled circumferentially with a shroud hanger including at least one hanger foot assembled within and between the segment hooks. The hanger foot includes a plurality of spaced apart hanger foot contact surfaces cooperating in juxtaposition with the contact surfaces of the shroud segment body radially outer surface and the hook end radially inner surfaces. The various contact surfaces cooperating in juxtaposition are matched in shape each to define a fluid choke therebetween.

    摘要翻译： 涡轮发动机护罩段，优选低延展性材料，例如陶瓷基质复合材料，包括在主体周向端部之间延伸的段体。 主体包括至少周向弧形的主体径向内表面，以及主体径向外表面，多个钩从该径向外表面大致径向向外延伸。 每个钩包括大致径向向外延伸的钩臂，具有大致轴向延伸的钩端，其具有与主体径向外表面的一部分间隔开并置的大致径向内表面。 这种主体外表面包括至少两个身体接触表面，每个至少两个身体接触表面的形状和形状至少在身体周向端部处并置，并具有配合的衣架接触表面。 每个钩端的径向内表面包括至少在该表面的周向中间部分中与配合的衣架接触面匹配的钩端接触表面。 在涡轮发动机护罩组件中，多个这样的护罩段与护罩悬挂器圆周地组装，护罩悬挂器包括组装在段钩内部和之间的至少一个衣架脚。 衣架脚包括多个间隔开的衣架脚接触表面，其与护罩段主体的径向外表面和钩端径向内表面的接触表面并置配合。 并列配合的各个接触表面的形状各自在其间形成流体扼流圈。

    Mounting assembly for igniter in a gas turbine engine combustor having a ceramic matrix composite liner
    6.
    发明授权
    Mounting assembly for igniter in a gas turbine engine combustor having a ceramic matrix composite liner 失效
    具有陶瓷基复合衬套的燃气涡轮发动机燃烧器中的点火器的安装组件

    公开(公告)号：US06920762B2

    公开(公告)日：2005-07-26

    申请号：US10341850

    申请日：2003-01-14

    申请人： Thomas Allen Wells ,  David Edward Bulman ,  Mark Eugene Noe ,  Harold Ray Hansel ,  Christopher Charles Glynn

    发明人： Thomas Allen Wells ,  David Edward Bulman ,  Mark Eugene Noe ,  Harold Ray Hansel ,  Christopher Charles Glynn

    IPC分类号： F02C7/264 ,  F16F3/04 ,  F23R3/60 ,  F02C7/266

    CPC分类号： F16F3/04 ,  F02C7/264 ,  F23D2207/00 ,  F23D2211/00 ,  F23R3/60 ,  F23R2900/00012

    摘要： An assembly for mounting an igniter in a gas turbine engine combustor between an outer casing and an outer liner, wherein a longitudinal centerline axis extends through the gas turbine engine. The igniter mounting assembly includes a first spring member encircling a portion of said igniter and being positioned between a surface adjacent the outer casing and an outer surface of the outer liner, a first ring member connected to a first end of the first spring member adjacent the outer surface of the outer liner, and a second ring member connected to a second end of the first spring member adjacent the surface adjacent the outer casing. Accordingly, the igniter is able to maintain substantial alignment with respect to an opening in the outer liner while moving radially and/or axially with respect to the outer liner as the outer casing experiences thermal growth greater than the outer liner.

    摘要翻译： 一种用于将燃气涡轮发动机燃烧器中的点火器安装在外壳和外衬套之间的组件，其中纵向中心线轴线延伸穿过燃气涡轮发动机。 点火器安装组件包括围绕所述点火器的一部分并且位于邻近外壳的表面和外衬套的外表面之间的第一弹簧构件，与第一弹簧构件的第一端相邻的第一环构件， 外衬套的外表面和与邻近外壳的表面相邻的第一弹簧构件的第二端连接的第二环构件。 因此，随着外套经历大于外衬套的热生长，点火器能够相对于外衬套的开口保持基本对准，同时相对于外衬套径向和/或轴向移动。

    Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor
    7.
    发明授权
    Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor 有权
    用于燃气涡轮发动机燃烧器中的陶瓷基体复合衬套的后端的密封组件

    公开(公告)号：US06895757B2

    公开(公告)日：2005-05-24

    申请号：US10361456

    申请日：2003-02-10

    申请人： Krista Anne Mitchell ,  David Edward Bulman ,  Mark Eugene Noe ,  Harold Ray Hansel ,  Christopher Charles Glynn ,  John David Bibler

    发明人： Krista Anne Mitchell ,  David Edward Bulman ,  Mark Eugene Noe ,  Harold Ray Hansel ,  Christopher Charles Glynn ,  John David Bibler

    IPC分类号： F01D11/00 ,  F23R3/00 ,  F23R3/50 ,  F23R3/60 ,  F02C7/20

    CPC分类号： F23R3/50 ,  F01D11/005 ,  F23R3/007 ,  F23R3/60

    摘要： An assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine including a longitudinal centerline axis extending therethrough. The sealing assembly includes a substantially annular first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end and a substantially annular second sealing member positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion. Accordingly, the first sealing member is maintained in its seated position as the support member aft portion moves radially with respect to the liner aft end and the second sealing member is maintained in its seated position as the support member aft portion moves axially with respect to the turbine nozzle. The first and second sealing members are also maintained in their respective seating positions as the support member aft portion moves axially with respect to the liner aft end and radially with respect to the turbine nozzle.

    摘要翻译： 一种用于在用于燃气涡轮发动机的燃烧器衬套的后端处提供密封件的组件，其包括从其延伸穿过的纵向中心线轴线。 密封组件包括位于支撑构件的后部和衬里后端之间的基本上环形的第一密封构件，以便位于衬套后端的指定表面部分上，并且基本上环形的第二密封构件位于支撑构件 后部部分和位于衬里后端的下游的涡轮喷嘴，以便位于支撑构件后部的指定表面部分上。 因此，当支撑构件后部相对于衬套后端径向移动时，第一密封构件保持在其就座位置，并且当支撑构件后部相对于衬套后端轴向移动时，第二密封构件保持在其就座位置 涡轮喷嘴。 第一和第二密封构件也保持在它们各自的就座位置，因为支撑构件后部相对于衬套后端轴向移动并相对于涡轮喷嘴径向移动。

    PITCH CHANGE APPARATUS FOR COUNTER-ROTATING PROPELLERS
    8.
    发明申请
    PITCH CHANGE APPARATUS FOR COUNTER-ROTATING PROPELLERS 有权
    用于逆转螺旋桨的换刀装置

    公开(公告)号：US20120079809A1

    公开(公告)日：2012-04-05

    申请号：US12894600

    申请日：2010-09-30

    申请人： Christopher Charles Glynn ,  Darek Tomasz Zatorski ,  Donald Scott Yeager ,  Nicholas Rowe Dinsmore ,  Jeffrey Raymond Menard ,  Brandon Wayne Miller

    发明人： Christopher Charles Glynn ,  Darek Tomasz Zatorski ,  Donald Scott Yeager ,  Nicholas Rowe Dinsmore ,  Jeffrey Raymond Menard ,  Brandon Wayne Miller

    IPC分类号： F02K3/00 ,  B64C11/06

    CPC分类号： B64C11/38 ,  B64C11/48 ,  B64D2027/005 ,  B64D2027/026 ,  Y02T50/66

    摘要： Axially spaced apart counter-rotatable forward and aft rows of forward and aft propellers mounted on forward and aft rotatable frames includes a flowpath passing through the forward and aft rotatable frames. Hydraulic rotary forward and aft pitch change actuators mounted on the aft rotatable frames are connected to and operable for controlling and setting pitch of the aft propellers. The pitch change actuators are mounted radially inwardly of the flowpath in a one to one ratio with forward and aft rotatable struts extending radially across the flowpath. One or more rotatable shafts extend through one or more of the rotatable struts and connect one or more of the pitch change actuators to one or more of the propellers. The pitch change actuators may be ganged together by unison rings having ring teeth engaging gear teeth on gears connected to the pitch change actuators or connected to the rotatable shafts.

    摘要翻译： 安装在前后可旋转框架上的前后后推螺旋桨的前后旋转的轴向间隔开的排列包括通过前后可旋转框架的流路。 安装在后部可旋转框架上的液压旋转前后变桨促动器连接到并可操作以控制和设定后推螺旋桨的桨距。 变桨促动器以一比一的比例径向向内安装有流动路径的向前和向后的可旋转支柱，径向延伸穿过流路。 一个或多个可旋转的轴延伸穿过可旋转支柱中的一个或多个，并将一个或多个俯仰变化致动器连接到一个或多个螺旋桨。 间距变换执行器可以通过一致的环组合在一起，所述环具有环形齿，其与连接到变桨致动器的齿轮啮合齿轮齿，或连接到可旋转轴。

    HYDRAULIC SYSTEM FOR FAN PITCH CHANGE ACTUATION OF COUNTER-ROTATING PROPELLERS
    9.
    发明申请
    HYDRAULIC SYSTEM FOR FAN PITCH CHANGE ACTUATION OF COUNTER-ROTATING PROPELLERS 有权
    用于风扇切换的液压系统改变旋转螺旋桨

    公开(公告)号：US20120079808A1

    公开(公告)日：2012-04-05

    申请号：US12894578

    申请日：2010-09-30

    申请人： Christopher Charles Glynn ,  Darek Tomasz Zatorski ,  Donald Scott Yeager ,  Nicholas Rowe Dinsmore ,  Jeffrey Raymond Menard ,  Brandon Wayne Miller

    发明人： Christopher Charles Glynn ,  Darek Tomasz Zatorski ,  Donald Scott Yeager ,  Nicholas Rowe Dinsmore ,  Jeffrey Raymond Menard ,  Brandon Wayne Miller

    IPC分类号： F02K3/00 ,  B64C11/06

    CPC分类号： F01D7/00 ,  B64D2027/005 ,  B64D2027/026 ,  F02C6/206 ,  F05D2220/324 ,  F05D2260/74 ,  F05D2260/79 ,  Y02T50/66

    摘要： Spaced apart counter-rotatable forward and aft rows of forward and aft propellers are mounted on forward and aft rotatable frames. Hydraulic rotary forward and aft pitch change actuators on the frames are operable for controlling pitch of the propellers. A hydraulic fluid supply outboard of the frames is connected to forward and aft rotary unions which are operable for transferring hydraulic fluid between forward and aft union stators to forward and aft union rotors mounted within the forward and aft rotary unions. The forward union rotor is operable to transfer the hydraulic fluid from the forward rotary union to the aft pitch change actuators and the aft union rotor is operable to transfer the hydraulic fluid from the aft rotary unions to the forward pitch change actuators. The forward and aft rotatable frames counter-rotatably mounted on a structural frame located forward or aft of the propellers.

    摘要翻译： 可分离的反向旋转的前后排螺旋桨的前排和后排分别安装在前后可旋转的框架上。 框架上的液压旋转前后变桨促动器可操作用于控制螺旋桨的桨距。 框架外侧的液压流体供应装置连接到前后旋转接头，其可操作用于将前后联动定子之间的液压流体传送到安装在前后旋转接头内的前后联接转子。 前进联合转子可操作以将液压流体从前部旋转联接器传递到后部变桨促动器，并且后部联接转子可操作以将液压流体从后部旋转接头传递到前部变桨促动器。 前后可旋转框架可反转地安装在位于螺旋桨前方或后方的结构框架上。