公开(公告)号：US08147192B2

公开(公告)日：2012-04-03

申请号：US12233847

申请日：2008-09-19

申请人： Daniel Vern Jones ,  James Harvey Laflen ,  Richard William Albrecht ,  Dustin Alfred Placke ,  Ching-Pang Lee

发明人： Daniel Vern Jones ,  James Harvey Laflen ,  Richard William Albrecht ,  Dustin Alfred Placke ,  Ching-Pang Lee

IPC分类号： F01D5/20 ,  F01D11/08

CPC分类号： F01D25/246 ,  F01D11/24 ,  F05D2240/11 ,  Y02T50/671

摘要： A turbine shroud includes a shroud hanger having an arcuate panel from which three inner hooks extend inwardly, and from which two outer hooks extend outwardly therefrom. The two outer hooks effect a statically determinate configuration of the shroud.

摘要翻译： 涡轮机罩包括具有弓形面板的护罩悬挂器，三个内钩从该拱形板向内延伸，两个外钩从其中向外延伸。 两个外钩影响护罩的静态结构。

公开(公告)号：US20100074745A1

公开(公告)日：2010-03-25

申请号：US12233847

申请日：2008-09-19

申请人： Daniel Vern Jones ,  James Harvey Laflen ,  Richard William Albrecht ,  Dustin Alfred Placke ,  Ching-Pang Lee

发明人： Daniel Vern Jones ,  James Harvey Laflen ,  Richard William Albrecht ,  Dustin Alfred Placke ,  Ching-Pang Lee

IPC分类号： F01D9/04

CPC分类号： F01D25/246 ,  F01D11/24 ,  F05D2240/11 ,  Y02T50/671

摘要： A turbine shroud includes a shroud hanger having an arcuate panel from which three inner hooks extend inwardly, and from which two outer hooks extend outwardly therefrom. The two outer hooks effect a statically determinate configuration of the shroud.

摘要翻译： 涡轮机罩包括具有弓形面板的护罩悬挂器，三个内钩从该拱形板向内延伸，两个外钩从其中向外延伸。 两个外钩影响护罩的静态结构。

公开(公告)号：US07690885B2

公开(公告)日：2010-04-06

申请号：US11565472

申请日：2006-11-30

申请人： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Vern Jones

发明人： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Vern Jones

IPC分类号： F01D25/12

CPC分类号： F01D11/08 ,  F01D11/10 ,  F05D2240/11 ,  F05D2260/202 ,  Y02T50/676

摘要： A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip. Post impingement cooling air is directed at the forward face to facilitate forming a film cooling layer on the shroud segment. The film cooling layer is shielded from combustion gases flowing through the gas turbine engine.

摘要翻译： 一种用于冷却燃气涡轮发动机的护罩区段的方法包括提供一种涡轮机护罩组件，其包括具有限定前表面的前缘的护罩区段。 涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的前表面和前表面之间限定间隙，其中形成在后表面上的唇缘相对于间隙径向向内定位 并且从所述间隙基本轴向地延伸到下游。 冷却空气被引导到间隙中。 离开间隙的冷却空气撞击唇缘。 后冲击冷却空气指向前面，以便于在护罩段上形成薄膜冷却层。 膜冷却层与流过燃气涡轮发动机的燃烧气体屏蔽。