公开(公告)号：US07293957B2

公开(公告)日：2007-11-13

申请号：US11692505

申请日：2007-03-28

申请人： Charlie Ellis ,  David Parker ,  J. Page Strohl ,  David Medrano

发明人： Charlie Ellis ,  David Parker ,  J. Page Strohl ,  David Medrano

IPC分类号： F01D9/04

CPC分类号： F01D9/041 ,  F01D11/005 ,  F05D2260/941

摘要： A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing its resistance to thermal deflection. This is accomplished by placing an opening along the innermost vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.

摘要翻译： 公开了一种用于燃气涡轮发动机的叶片组件，其具有较低的热致应力，导致改进的部件耐久性。 叶片组件翼型中的应力通过增加叶片平台的柔性并降低其对热偏转的抵抗力而降低。 这是通过沿着最内侧叶片组装轨道放置开口来实现的，该开口减小了平台的有效刚度，从而降低了叶片组件的翼型件中的操作应力。 然后将可拆卸密封件放置在开口中，以防止不期望的泄漏，同时保持增加的平台灵活性的益处。

公开(公告)号：US20080148737A1

公开(公告)日：2008-06-26

申请号：US11614329

申请日：2006-12-21

申请人： Charlie Ellis ,  J. Page Strohl ,  Matt Thomas

发明人： Charlie Ellis ,  J. Page Strohl ,  Matt Thomas

IPC分类号： F02C7/20 ,  F01D11/00

CPC分类号： F01D25/246 ,  F01D11/08 ,  F05D2240/11 ,  F05D2240/57

摘要： A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending slots are placed in the segments to reduce stiffness. In order to minimize air leakage through the support ring, generally circumferential slots are placed in the ring and connect with the generally radially extending slots. Positioned in each of the generally radially extending slots and generally circumferential slots, and in contact with each other, are two sheet metal plates. The plates are staked to the support ring structure so as to provide a seal member, yet compensate for thermal growth.

摘要翻译： 公开了具有减少的泄漏空气的涡轮机静态结构。 公开了一种具有很少段的静态结构的涡轮机支撑环，其中段具有改善的热膨胀能力，并且减少了空气泄漏。 多个径向延伸的槽被放置在段中以降低刚度。 为了最小化通过支撑环的空气泄漏，大体上圆周槽被放置在环中并与大致径向延伸的狭槽连接。 位于每个大致径向延伸的狭槽和大致圆周的狭槽中并且彼此接触的是两个金属板。 板被固定到支撑环结构上，以便提供密封构件，而补偿热生长。

公开(公告)号：US07958735B2

公开(公告)日：2011-06-14

申请号：US11614329

申请日：2006-12-21

申请人： Charlie Ellis ,  J. Page Strohl ,  Matt Thomas

发明人： Charlie Ellis ,  J. Page Strohl ,  Matt Thomas

IPC分类号： F01D9/04

CPC分类号： F01D25/246 ,  F01D11/08 ,  F05D2240/11 ,  F05D2240/57

摘要： A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending slots are placed in the segments to reduce stiffness. In order to minimize air leakage through the support ring, generally circumferential slots are placed in the ring and connect with the generally radially extending slots. Positioned in each of the generally radially extending slots and generally circumferential slots, and in contact with each other, are two sheet metal plates. The plates are staked to the support ring structure so as to provide a seal member, yet compensate for thermal growth.

摘要翻译： 公开了具有减少的泄漏空气的涡轮机静态结构。 公开了一种具有很少段的静态结构的涡轮机支撑环，其中段具有改善的热膨胀能力，并且减少了空气泄漏。 多个径向延伸的槽被放置在段中以降低刚度。 为了最小化通过支撑环的空气泄漏，大体上圆周槽被放置在环中并与大致径向延伸的狭槽连接。 位于每个大致径向延伸的狭槽和大致圆周的狭槽中并且彼此接触的是两个金属板。 板被固定到支撑环结构上，以便提供密封构件，而补偿热生长。

公开(公告)号：US08104290B2

公开(公告)日：2012-01-31

申请号：US12251973

申请日：2008-10-15

申请人： Charlie Ellis ,  Carlos Calderon

发明人： Charlie Ellis ,  Carlos Calderon

IPC分类号： F02C7/20

CPC分类号： F16F1/025 ,  F23R3/60

摘要： The present invention are directed towards a system and method for providing a way of reducing the vibrations and wear between mating components of a gas turbine combustor. The gas turbine combustor includes a flow sleeve having a plurality of liner stops and a combustion liner located radially within the flow sleeve. Spring dampers are positioned between the combustion liner and the flow sleeve to restrict the relative movement between the flow sleeve and the combustion liner and dampen vibrations at their assembly location. The spring dampers are capable of compressing to permit thermal growth between the combustion liner and flow sleeve.

摘要翻译： 本发明涉及一种用于提供减少燃气轮机燃烧器的配合部件之间的振动和磨损的方法的系统和方法。 燃气轮机燃烧器包括具有多个衬套止挡件和径向位​​于流动套管内的燃烧衬套的流动套管。 弹簧阻尼器位于燃烧衬套和流动套筒之间，以限制流动套筒和燃烧衬套之间的相对运动并且在其组装位置处抑制振动。 弹簧阻尼器能够压缩以允许燃烧衬套和流动套筒之间的热量生长。

公开(公告)号：US20100089068A1

公开(公告)日：2010-04-15

申请号：US12251973

申请日：2008-10-15

申请人： Charlie Ellis ,  Carlos Calderon

发明人： Charlie Ellis ,  Carlos Calderon

IPC分类号： F23R3/60 ,  F02C7/20 ,  F16F7/00

CPC分类号： F16F1/025 ,  F23R3/60

摘要： The present invention are directed towards a system and method for providing a way of reducing the vibrations and wear between mating components of a gas turbine combustor. The gas turbine combustor includes a flow sleeve having a plurality of liner stops and a combustion liner located radially within the flow sleeve. Spring dampers are positioned between the combustion liner and the flow sleeve to restrict the relative movement between the flow sleeve and the combustion liner and dampen vibrations at their assembly location. The spring dampers are capable of compressing to permit thermal growth between the combustion liner and flow sleeve.

摘要翻译： 本发明涉及一种用于提供减少燃气轮机燃烧器的配合部件之间的振动和磨损的方法的系统和方法。 燃气轮机燃烧器包括具有多个衬套止挡件和径向位​​于流动套管内的燃烧衬套的流动套管。 弹簧阻尼器位于燃烧衬套和流动套筒之间，以限制流动套筒和燃烧衬套之间的相对运动并且在其组装位置处抑制振动。 弹簧阻尼器能够压缩以允许燃烧衬套和流动套筒之间的热量生长。

公开(公告)号：US08001789B2

公开(公告)日：2011-08-23

申请号：US12055485

申请日：2008-03-26

申请人： Santiago Vega ,  Charlie Ellis ,  Roger Kastelic ,  James Leahy ,  Janak Raguraman

发明人： Santiago Vega ,  Charlie Ellis ,  Roger Kastelic ,  James Leahy ,  Janak Raguraman

IPC分类号： F02C7/04

CPC分类号： F02C6/08 ,  F02C7/047

摘要： An improved inlet bleed heat system for a gas turbine engine is disclosed. The inlet bleed heat system provides improved mixing in an inlet region while permitting the engine to be operated at lower power settings. The inlet bleed heat system comprises a supply conduit, a plurality of feed tubes extending from the supply conduit, and a guide tube for receiving opposing ends of the feed tubes. The plurality of feed tubes each have a plurality of injection orifices and the feed tubes are oriented such that the injection orifices generally face into a flow of oncoming air with the feed tubes being positioned forward of a plurality of sound attenuating baffles.

摘要翻译： 公开了一种用于燃气涡轮发动机的改进的入口放气加热系统。 入口放气加热系统在入口区域提供改进的混合，同时允许发动机在较低功率设置下操作。 入口放气加热系统包括供应管道，从供应管道延伸的多个进料管和用于接收进料管的相对端的引导管。 多个进料管各自具有多个喷射孔，并且进料管被定向成使得喷射孔通常面向迎面而来的空气流，其中进料管位于多个声音衰减挡板的前方。