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1. 发明申请

US20160177723A1 TURBINE AIRFOIL WITH OPTIMIZED AIRFOIL ELEMENT ANGLES 有权
标题翻译：具有优化的气翼单元角的涡轮机空气
公开(公告)号：US20160177723A1
公开(公告)日：2016-06-23
申请号：US14949991
申请日：2015-11-24
申请人： Siemens Energy, Inc.
发明人： Andrew S. Lohaus , Anthony J. Malandra , Carmen Andrew Scribner , Farzad Taremi , Horia Flitan , Ching-Pang Lee , Gm Salam Azad , Tobias Buchal
IPC分类号： F01D1/04
CPC分类号： F01D9/041 , F01D5/141 , F05D2250/74
摘要： A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 2, 3, and 4.
摘要翻译：一种用于安装在燃气涡轮发动机中的涡轮机翼型组件。翼型组件包括端壁和从端壁径向向外延伸的翼型件。翼型件包括压力和抽吸侧壁，其限定翼型的弦向间隔开的前缘和后缘。机翼平均线被定义为位于压力和吸力侧壁之间的中心。平均线与平行于前缘和后缘的发动机轴线的直线之间的角度限定了气流入口角α和出口角度＆bgr。翼型件的入口角和出口角度基本上与表1，图2，图3和图4中的一个所示的入口角度值α和出口角度值bgr相符。

2. 发明申请

US20180066523A1 TWO PRESSURE COOLING OF TURBINE AIRFOILS 审中-公开
公开(公告)号：US20180066523A1
公开(公告)日：2018-03-08
申请号：US15558343
申请日：2015-04-06
申请人： Siemens Energy, Inc.
发明人： Jan H. Marsh , John J. Marra , Carmen Andrew Scribner
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D5/186 , F01D5/187 , F01D25/12 , F05D2220/32 , F05D2240/301 , F05D2260/202
摘要： An airfoil cooling system (54) for a gas turbine engine (10) is disclosed. The airfoil cooling system (54) may be formed from at least a first cooling fluid supply system (56), and a second cooling fluid supply system (58). The first cooling fluid supply system (56) may be configured to supply cooling fluids at a first pressure to one or more airfoils of a first row (68) of airfoils, and the second cooling fluid supply system (58) may be configured to supply cooling fluids at a second pressure to the one or more airfoils of the first row (68) of airfoils. Additionally, the second pressure may be lower than the first pressure. As such, each of the one or more airfoils may be cooled by cooling fluids at two different pressures. In particular embodiments, this may allow the airfoils to be cooled, while lowering the cost to the turbine engine (10) for providing such cooling.

3. 发明授权

US09797267B2 Turbine airfoil with optimized airfoil element angles 有权
公开(公告)号：US09797267B2
公开(公告)日：2017-10-24
申请号：US14949991
申请日：2015-11-24
申请人： Siemens Energy, Inc.
发明人： Andrew S. Lohaus , Anthony J. Malandra , Carmen Andrew Scribner , Farzad Taremi , Horia Flitan , Ching-Pang Lee , Gm Salam Azad , Tobias Buchal
IPC分类号： F01D1/04 , F01D9/04 , F01D5/14
CPC分类号： F01D9/041 , F01D5/141 , F05D2250/74
摘要： A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 2, 3, and 4.

4. 发明授权

US09797259B2 Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids 有权
公开(公告)号：US09797259B2
公开(公告)日：2017-10-24
申请号：US14200168
申请日：2014-03-07
申请人： Siemens Energy, Inc.
发明人： Jan H. Marsh , Stephen John Messmann , Carmen Andrew Scribner
IPC分类号： F01D5/18 , F01D25/14 , F01D5/08 , F01D5/22
CPC分类号： F01D5/187 , F01D5/081 , F01D5/087 , F01D5/22 , F01D25/14 , F05D2240/81
摘要： A turbine airfoil cooling system including a low pressure cooling system and a high pressure cooling system for a turbine airfoil of a gas turbine engine is disclosed. In at least one embodiment, the low pressure cooling system may be an ambient air cooling system, and the high pressure cooling system may be a compressor bleed air cooling system. In at least one embodiment, the compressor bleed air cooling system in communication with a high pressure subsystem that may be a snubber cooling system positioned within a snubber. A delivery system including a movable air supply tube may be used to separate the low and high pressure cooling subsystems. The delivery system may enable high pressure cooling air to be passed to the snubber cooling system separate from low pressure cooling fluid supplied by the low pressure cooling system to other portions of the turbine airfoil cooling system.

5. 发明授权

US09435212B2 Turbine airfoil with laterally extending snubber having internal cooling system 有权
标题翻译：具有横向延伸缓冲器的涡轮机翼具有内部冷却系统
公开(公告)号：US09435212B2
公开(公告)日：2016-09-06
申请号：US14074930
申请日：2013-11-08
申请人： Siemens Energy, Inc.
发明人： Carmen Andrew Scribner , Stephen John Messmann , Jan H. Marsh
IPC分类号： F01D5/18 , F01D5/22 , F01D5/30
CPC分类号： F01D5/188 , F01D5/187 , F01D5/22 , F01D5/3007 , F05D2260/201
摘要： A turbine airfoil usable in a turbine engine and having at least one snubber with a snubber cooling system positioned therein and in communication with an airfoil cooling system is disclosed. The snubber may extend from the outer housing of the airfoil toward an adjacent turbine airfoil positioned within a row of airfoils. The snubber cooling system may include an inner cooling channel separated from an outer cooling channel by an inner wall. The inner wall may include a plurality of impingement cooling orifices that direct impingement fluid against an outer wall defining the outer cooling channel. In one embodiment, the cooling fluids may be exhausted from the snubber, and in another embodiment, the cooling fluids may be returned to the airfoil cooling system. Flow guides may be positioned in the outer cooling channel, which may reduce cross-flow by the impingement orifices, thereby increasing effectiveness.
摘要翻译：公开了一种可用于涡轮发动机并且具有至少一个具有缓冲冷却系统的缓冲器并且与翼型件冷却系统连通的涡轮机翼型。缓冲器可以从翼型的外壳延伸到位于一排翼型内的相邻的涡轮机翼型。缓冲冷却系统可以包括通过内壁与外部冷却通道分离的内部冷却通道。内壁可以包括多个冲击冷却孔，其将冲击流体引导到限定外部冷却通道的外壁。在一个实施例中，冷却流体可以从缓冲器排出，并且在另一个实施例中，冷却流体可以返回到翼型冷却系统。流动引导件可以定位在外部冷却通道中，这可以减少冲击孔的交叉流动，从而增加效率。

6. 发明申请

US20150252688A1 TURBINE AIRFOIL COOLING SYSTEM WITH COOLING SYSTEMS USING HIGH AND LOW PRESSURE COOLING FLUIDS 有权
标题翻译：具有冷却系统的涡轮机空气冷却系统，使用高压低压冷却液
公开(公告)号：US20150252688A1
公开(公告)日：2015-09-10
申请号：US14200168
申请日：2014-03-07
申请人： Siemens Energy, Inc.
发明人： Jan H. Marsh , Stephen John Messmann , Carmen Andrew Scribner
IPC分类号： F01D25/14 , F01D5/18
CPC分类号： F01D5/187 , F01D5/081 , F01D5/087 , F01D5/22 , F01D25/14 , F05D2240/81
摘要： A turbine airfoil cooling system including a low pressure cooling system and a high pressure cooling system for a turbine airfoil of a gas turbine engine is disclosed. In at least one embodiment, the low pressure cooling system may be an ambient air cooling system, and the high pressure cooling system may be a compressor bleed air cooling system. In at least one embodiment, the compressor bleed air cooling system in communication with a high pressure subsystem that may be a snubber cooling system positioned within a snubber. A delivery system including a movable air supply tube may be used to separate the low and high pressure cooling subsystems. The delivery system may enable high pressure cooling air to be passed to the snubber cooling system separate from low pressure cooling fluid supplied by the low pressure cooling system to other portions of the turbine airfoil cooling system.
摘要翻译：公开了一种包括低压冷却系统和用于燃气涡轮发动机的涡轮叶片的高压冷却系统的涡轮机翼型冷却系统。在至少一个实施例中，低压冷却系统可以是环境空气冷却系统，并且高压冷却系统可以是压缩机排气冷却系统。在至少一个实施例中，与高压子系统连通的压缩机排气冷却系统可以是位于缓冲器内的缓冲冷却系统。可以使用包括可移动空气供应管的输送系统来分离低压和高压冷却子系统。输送系统可以使高压冷却空气能够被传递到缓冲冷却系统，该低温冷却系统与由低压冷却系统供应的低压冷却流体分离到涡轮机翼型冷却系统的其它部分。

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