公开(公告)号：US07625174B2

公开(公告)日：2009-12-01

申请号：US11303884

申请日：2005-12-16

Applicant: Vincent Marion Drerup ,  Harold Ray Hansel ,  Ching-Pang Lee

Inventor： Vincent Marion Drerup ,  Harold Ray Hansel ,  Ching-Pang Lee

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D11/005 ,  F05D2240/57 ,  F05D2260/30 ,  F05D2260/33 ,  Y02T50/673

Abstract: A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one catch to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that a portion of the at least one spline seal is received within a recess defined within the turbine nozzle slot to facilitate retaining the at least one spline seal within the turbine nozzle slot.

Abstract translation: 提供一种用于组装燃气涡轮发动机的方法。 该方法包括将第一涡轮喷嘴联接在发动机内，将第二涡轮喷嘴与第一涡轮喷嘴周向相邻地连接，使得在第一涡轮喷嘴和第二涡轮喷嘴之间限定间隙，并提供包括基本上平面的主体的至少一个花键密封。 该方法还包括形成至少一个止动件以从至少一个花键密封件的本体部分向外延伸，以及将至少一个花键密封件插入到限定在第一和第二涡轮喷嘴中的至少一个中的狭槽中，以便减少 泄漏通过所述间隙，使得所述至少一个花键密封件的一部分被容纳在限定在所述涡轮喷嘴槽内的凹部内，以便于将所述至少一个花键密封件保持在所述涡轮喷嘴槽内。

公开(公告)号：US06397603B1

公开(公告)日：2002-06-04

申请号：US09567557

申请日：2000-05-05

Applicant: Wayne Garcia Edmondson ,  James Dale Steibel ,  Harold Ray Hansel

Inventor： Wayne Garcia Edmondson ,  James Dale Steibel ,  Harold Ray Hansel

IPC: F23R360

CPC classification number: F23R3/007 ,  F05B2230/606 ,  F23D2212/103 ,  F23R3/60

Abstract: A combustor having liners made from ceramic matrix composite materials (CMC's) that are capable of withstanding higher temperatures than metallic liners. The ceramic matrix composite liners are used in conjunction with mating components that are manufactured from superalloy materials. To permit the use of a combustor having liners made from CMC materials in conjunction with metallic materials used for the mating forward cowls, and aft seals with attached seal retainer over the broad range of temperatures of a combustor, the combustor is designed to allow for the differential thermal expansion of the differing materials at their interfaces in a manner that does not introduce stresses into the liner as a result of thermal expansion and also balances the flow of cooling air as a result of the thermal expansion.

Abstract translation: 具有由陶瓷基质复合材料（CMC）制成的衬垫的燃烧器能够承受比金属衬里更高的温度。 陶瓷基复合衬套与由超级合金材料制成的配合部件结合使用。 为了允许使用具有由CMC材料制成的衬垫与用于配合前罩的金属材料的燃烧器以及在燃烧器的宽范围的温度下具有附接的密封保持器的尾部密封件，燃烧器被设计成允许 不同材料在其界面处的不均匀热膨胀以不会由于热膨胀而将应力引入衬垫并且还由于热膨胀而平衡冷却空气的流动的方式。

公开(公告)号：US07575415B2

公开(公告)日：2009-08-18

申请号：US11271101

申请日：2005-11-10

Applicant: Vincent Marion Drerup ,  Harold Ray Hansel ,  James Anthony Ketzer ,  Ching-Pang Lee

Inventor： Vincent Marion Drerup ,  Harold Ray Hansel ,  James Anthony Ketzer ,  Ching-Pang Lee

IPC: F01D9/04

CPC classification number: F02C7/28 ,  F01D11/005 ,  F05D2240/12 ,  F05D2260/30 ,  Y10T29/49297 ,  Y10T29/4932 ,  Y10T29/49323

Abstract: A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one retainer tab to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through the gap, such that the at least one retainer tab facilitates retaining the retainer tab within the turbine nozzle slot.

Abstract translation: 提供一种用于组装燃气涡轮发动机的方法。 该方法包括将第一涡轮喷嘴联接在发动机内，将第二涡轮喷嘴与第一涡轮喷嘴周向相邻地连接，使得在第一涡轮喷嘴和第二涡轮喷嘴之间限定间隙，并提供包括基本上平面的主体的至少一个花键密封。 该方法还包括形成至少一个保持器突片以从至少一个花键密封件的主体部分向外延伸，以及将至少一个花键密封件插入限定在第一和第二涡轮喷嘴中的至少一个中的狭槽中，以便于 减少通过间隙的泄漏，使得至少一个保持器翼片有助于将保持器突片保持在涡轮喷嘴槽内。

公开(公告)号：US06904757B2

公开(公告)日：2005-06-14

申请号：US10324871

申请日：2002-12-20

Applicant: 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

Inventor： 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: F23R3/00 ,  F23R3/60 ,  F02C7/20

CPC classification number: F23R3/007 ,  F23R3/60

Abstract: 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.

Abstract translation: 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

公开(公告)号：US06775985B2

公开(公告)日：2004-08-17

申请号：US10342040

申请日：2003-01-14

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

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

IPC: F02C100

CPC classification number: F23R3/007 ,  F05B2230/606 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00014

Abstract: 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.

Abstract translation: 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：US06920762B2

公开(公告)日：2005-07-26

申请号：US10341850

申请日：2003-01-14

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

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

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

CPC classification number: F16F3/04 ,  F02C7/264 ,  F23D2207/00 ,  F23D2211/00 ,  F23R3/60 ,  F23R2900/00012

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US06895761B2

公开(公告)日：2005-05-24

申请号：US10326209

申请日：2002-12-20

Applicant: 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

Inventor： 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: F23R3/00 ,  F23R3/60 ,  F02C7/20

CPC classification number: F23R3/60 ,  F05B2230/606 ,  F23R3/007

Abstract: 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.

Abstract translation: 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

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

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

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

CPC classification number: F23R3/50 ,  F01D11/005 ,  F23R3/007 ,  F23R3/60

Abstract: 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.

Abstract translation: 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。