公开(公告)号：US06775985B2

公开(公告)日：2004-08-17

申请号：US10342040

申请日：2003-01-14

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

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

IPC分类号： F02C100

CPC分类号： F23R3/007 ,  F05B2230/606 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00014

摘要： A support assembly for a gas turbine engine combustor including an inner liner and an inner casing spaced therefrom, wherein a longitudinal centerline axis extends through the gas turbine engine. The support assembly includes an annular inner support cone located adjacent an aft end of said inner liner, an annular nozzle support connected to the inner support cone, and a plurality of support members connected at a first end to a forward end of the inner liner and connected at a second end to the inner support cone.

摘要翻译： 一种用于燃气涡轮发动机燃烧器的支撑组件，包括内衬和与其分开的内壳，其中纵向中心线轴线延伸穿过燃气涡轮发动机。 所述支撑组件包括邻近所述内衬的后端定位的环形内支撑锥体，连接到所述内支撑锥体的环形喷嘴支撑件以及在第一端连接到所述内衬垫的前端的多个支撑构件，以及 在第二端连接到内支撑锥体。

公开(公告)号：US06895761B2

公开(公告)日：2005-05-24

申请号：US10326209

申请日：2002-12-20

申请人： Krista Anne Mitchell ,  David Edward Bulman ,  Mark Eugene Noe ,  Harold Ray Hansel ,  Thomas Allen Wells ,  Christopher Charles Glynn ,  John David Bibler ,  Toby George Darkins, Jr. ,  Joseph John Charneski ,  Craig Patrick Burns

发明人： Krista Anne Mitchell ,  David Edward Bulman ,  Mark Eugene Noe ,  Harold Ray Hansel ,  Thomas Allen Wells ,  Christopher Charles Glynn ,  John David Bibler ,  Toby George Darkins, Jr. ,  Joseph John Charneski ,  Craig Patrick Burns

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

CPC分类号： F23R3/60 ,  F05B2230/606 ,  F23R3/007

摘要： A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

摘要翻译： 包括支撑构件的燃气涡轮发动机燃烧器的衬套的后端的安装组件，其中纵向中心线轴线延伸穿过燃气涡轮发动机。 安装组件包括销构件，其延伸穿过用于燃烧器的支撑构件的一部分中的多个周向间隔开的开口中的每一个并且形成在衬套的后端中的多个部分开口，每个销构件包括 在其一端的头部，以及位于支撑构件中的每个开口内的装置，以便将销构件保持在其中。 当支撑构件经历大于衬套的热生长时，销构件和支撑构件能够相对于衬垫后端部径向和/或轴向地滑动。

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。

公开(公告)号：US06904757B2

公开(公告)日：2005-06-14

申请号：US10324871

申请日：2002-12-20

申请人： Krista Anne Mitchell ,  David Edward Bulman ,  Mark Eugene Noe ,  Harold Ray Hansel ,  Thomas Allen Wells ,  Christopher Charles Glynn ,  John David Bibler ,  Toby George Darkins, Jr. ,  Joseph John Charneski ,  Craig Patrick Burns

发明人： Krista Anne Mitchell ,  David Edward Bulman ,  Mark Eugene Noe ,  Harold Ray Hansel ,  Thomas Allen Wells ,  Christopher Charles Glynn ,  John David Bibler ,  Toby George Darkins, Jr. ,  Joseph John Charneski ,  Craig Patrick Burns

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

CPC分类号： F23R3/007 ,  F23R3/60

摘要： A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings. In this way, the cowl aft portion and the dome portion are fixedly connected together between the bushing and the nut so that the bushings are able to slide radially through the openings in the liner forward end as the cowl and the dome experience thermal growth greater than the liner.

摘要翻译： 一种用于在包括圆顶和整流罩的燃气涡轮发动机的燃烧器中的衬套的前端的安装组件，其中纵向中心线轴线延伸穿过燃气涡轮发动机。 安装组件包括延伸穿过形成在衬套的前端中的多个周向间隔开的开口中的每一个的销构件，整流罩的后部和圆顶的一部分，每个销构件包括头部 其一端。 螺母可调节地连接到与头部相对的每个销构件的端部。 衬套位于每个销构件的位于头部部分和螺母之间的位置处，其中衬里前端中的开口的尺寸设置成适合围绕衬套。 以这种方式，整流罩后部和穹顶部分在衬套和螺母之间固定连接在一起，使得衬套能够径向滑过衬套前端中的开口，因为整流罩和穹顶经历热膨胀大于 班轮