公开(公告)号：US08403634B2

公开(公告)日：2013-03-26

申请号：US13216347

申请日：2011-08-24

申请人： Brian P. Arness ,  John E. Greene ,  Sze Bun B. Chan

发明人： Brian P. Arness ,  John E. Greene ,  Sze Bun B. Chan

IPC分类号： F01D9/04

CPC分类号： F01D9/041 ,  F01D11/005 ,  F01D25/246 ,  F05D2220/3212 ,  F05D2230/64 ,  F05D2240/57 ,  F05D2250/182 ,  F05D2260/30 ,  F05D2300/505

摘要： A retaining seal assembly for use in a gas turbine engine is provided. The retaining seal assembly comprises an outer retaining ring coupled to an aft end of a gas turbine engine combustor. A turbine nozzle is coupled to the outer retaining ring and comprises an outer band. The outer band comprises a leading edge and an opposing trailing edge that defines a slot. A retention seal comprises a first end positioned within the slot, a generally opposing second end that contacts the outer retaining ring, and a body extending between the first end and the second end. The body further comprises an insertion portion positioned within a passage formed in the outer band. The retention seal is fabricated from a resilient material and is configured to facilitate coupling the turbine nozzle to the outer retaining ring.

摘要翻译： 提供了一种用于燃气轮机的保持密封组件。 保持密封组件包括联接到燃气涡轮发动机燃烧器的后端的外保持环。 涡轮喷嘴连接到外保持环并且包括外带。 外带包括前缘和限定槽的相对的后缘。 保持密封件包括定位在槽内的第一端，与外保持环接触的大致相对的第二端，以及在第一端和第二端之间延伸的本体。 主体还包括位于形成在外带中的通道内的插入部分。 保持密封件由弹性材料制成并且构造成便于将涡轮喷嘴连接到外保持环。

公开(公告)号：US20110311353A1

公开(公告)日：2011-12-22

申请号：US13216347

申请日：2011-08-24

申请人： Brian P. Arness ,  John E. Greene ,  Sze Bun B. Chan

发明人： Brian P. Arness ,  John E. Greene ,  Sze Bun B. Chan

IPC分类号： F01D11/08

CPC分类号： F01D9/041 ,  F01D11/005 ,  F01D25/246 ,  F05D2220/3212 ,  F05D2230/64 ,  F05D2240/57 ,  F05D2250/182 ,  F05D2260/30 ,  F05D2300/505

摘要： A method for assembling a turbine nozzle assembly with respect to a combustor of a gas turbine engine is provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles is provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.

摘要翻译： 提供了一种用于组装相对于燃气涡轮发动机的燃烧器的涡轮喷嘴组件的方法。 该方法包括将径向外保持环联接到燃烧器的后端。 提供多个涡轮喷嘴。 每个涡轮喷嘴包括内带，径向相对的外带，以及在内带和外带之间延伸的至少一个叶片。 每个涡轮喷嘴的外带连接到外保持环以限定涡轮喷嘴组件。 内部保持环围绕燃气涡轮发动机的轴线定位并且联接到每个涡轮喷嘴的内部带。

公开(公告)号：US08038389B2

公开(公告)日：2011-10-18

申请号：US11325185

申请日：2006-01-04

申请人： Brian P. Arness ,  John E. Greene ,  Sze Bun B. Chan

发明人： Brian P. Arness ,  John E. Greene ,  Sze Bun B. Chan

IPC分类号： F01D9/04

CPC分类号： F01D9/041 ,  F01D11/005 ,  F01D25/246 ,  F05D2220/3212 ,  F05D2230/64 ,  F05D2240/57 ,  F05D2250/182 ,  F05D2260/30 ,  F05D2300/505

摘要： A turbine nozzle assembly and a method for assembling the turbine nozzle assembly with respect to a combustor of a gas turbine engine are provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles are provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.

摘要翻译： 提供了一种涡轮喷嘴组件和用于将涡轮喷嘴组件相对于燃气涡轮发动机的燃烧器组装的方法。 该方法包括将径向外保持环联接到燃烧器的后端。 提供多个涡轮喷嘴。 每个涡轮喷嘴包括内带，径向相对的外带，以及在内带和外带之间延伸的至少一个叶片。 每个涡轮喷嘴的外带连接到外保持环以限定涡轮喷嘴组件。 内部保持环围绕燃气涡轮发动机的轴线定位并且联接到每个涡轮喷嘴的内部带。