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1. 发明授权

US06413044B1 Blade cooling in gas turbine 失效
标题翻译：燃气轮机叶片冷却
公开(公告)号：US06413044B1
公开(公告)日：2002-07-02
申请号：US09609052
申请日：2000-06-30
申请人： Norman Roeloffs , Wesley D. Brown
发明人： Norman Roeloffs , Wesley D. Brown
IPC分类号： F04D2970
CPC分类号： F01D5/187 , F01D25/32 , F05D2250/314 , F05D2250/322 , F05D2250/52 , F05D2260/205 , F05D2260/607
摘要： A gas turbine whose blades are cooled with cooling air has in its turbine part a device for the removal of dirt particles from the cooling air. The device consists of a first chamber in which the cooling air is collected, and a second chamber into which the cooling air from the first chamber is fed through conduit, and in which the dirt particles are removed from the cooling air. The conduit, above which a drop in pressure occurs, are oriented at an angle (&phgr;) in relation to the rotor axis so that the cooling air is accelerated in the tangential direction in relation to the rotor and moves in the circumferential direction of the rotor within the second chamber. Dirt particles are removed in the second chamber by centrifugal force from the cooling air in that they are driven outward and pass through the outlet openings into the gas stream of the turbine. The clean cooling air exits through radially further inward outlet openings into the cooling channels of the blades.
摘要翻译：其叶片用冷却空气冷却的燃气轮机在其涡轮机部分具有用于从冷却空气中除去污垢颗粒的装置。该装置包括收集冷却空气的第一室和第二室，来自第一室的冷却空气通过第二室被供给到导管中，并且其中灰尘颗粒从冷却空气中除去。导致压力下降的导管相对于转子轴线以角度（phi）取向，使得冷却空气相对于转子沿切线方向加速并沿转子的圆周方向移动在第二个房间内。通过来自冷却空气的离心力在第二室中除去污垢颗粒，因为它们被向外驱动，并通过出口开口进入涡轮机的气流。清洁的冷却空气通过径向进一步向内的出口进入叶片的冷却通道。

2. 发明申请

US20060269410A1 Turbine blade cooling system 有权
标题翻译：涡轮叶片冷却系统
公开(公告)号：US20060269410A1
公开(公告)日：2006-11-30
申请号：US11140786
申请日：2005-05-31
申请人： James Downs , Norman Roeloffs , Edward Pietraszkiewicz
发明人： James Downs , Norman Roeloffs , Edward Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/711 , F05D2250/712 , F05D2260/201 , F05D2260/202
摘要： A turbine blade cooling system for a gas turbine engine includes a turbine blade having a trailing edge, a concave side, and a convex side. The trailing edge defines at least one set of impingement holes each having a central longitudinal axis which is closer to a nearest portion of an edge of the blade at one of the concave and convex sides relative to a nearest portion of an edge of the blade at the other of the concave and convex sides. Alternatively or in addition to the foregoing, the trailing edge can define at least one set of impingement holes each having a central longitudinal axis which is angled in a direction of a flow of cooling medium toward one of the concave and convex sides relative to the other of the concave and convex sides.
摘要翻译：用于燃气涡轮发动机的涡轮叶片冷却系统包括具有后缘，凹侧和凸侧的涡轮叶片。后缘限定至少一组冲击孔，每组冲击孔具有中心纵向轴线，该中心纵向轴线相对于叶片的边缘的最近部分在相对于叶片的边缘的最近部分处于相对于叶片的边缘的最靠近部分处更靠近叶片的边缘的最近部分另一个凹凸边。或者或除了上述之外，后缘可以限定至少一组冲击孔，每组冲击孔具有中心纵向轴线，所述中心纵向轴线在冷却介质的流动方向上相对于另一组的凹凸侧面的凹凸边。

3. 发明申请

US20070140848A1 Cooled turbine blade 有权
标题翻译：冷却涡轮叶片
公开(公告)号：US20070140848A1
公开(公告)日：2007-06-21
申请号：US11303593
申请日：2005-12-15
申请人： Robert Charbonneau , James Downs , Shawn Gregg , Wesley Harris , Natalia Khandros , Jeffrey Levine , Paul Orndoff , Steve Palmer , Edward Pietraszkiewicz , Norman Roeloffs , Richard Stockton , Wanda Widmer , Dagny Williams
发明人： Robert Charbonneau , James Downs , Shawn Gregg , Wesley Harris , Natalia Khandros , Jeffrey Levine , Paul Orndoff , Steve Palmer , Edward Pietraszkiewicz , Norman Roeloffs , Richard Stockton , Wanda Widmer , Dagny Williams
IPC分类号： F01D5/18
CPC分类号： F01D5/081 , F01D5/143 , F01D5/145 , F01D5/187 , F01D5/20 , F05D2240/122 , F05D2240/304 , F05D2240/80 , F05D2250/185 , F05D2250/232 , F05D2250/314 , F05D2250/712 , F05D2260/607
摘要： A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.
摘要翻译：诸如涡轮叶片的涡轮发动机部件具有翼型部分，在翼型部分内的多个冷却通道，每个冷却通道具有用于冷却流体的入口。每个入口具有喇叭口口部分。涡轮发动机部件还可以在翼型部分的尖端处具有污物漏斗，具有至少一个倾斜边缘的平台和底切后缘槽。

4. 发明授权

US06527514B2 Turbine blade with rub tolerant cooling construction 有权
标题翻译：涡轮叶片具有耐磨冷却结构
公开(公告)号：US06527514B2
公开(公告)日：2003-03-04
申请号：US09877083
申请日：2001-06-11
申请人： Norman Roeloffs
发明人： Norman Roeloffs
IPC分类号： F04D2958
CPC分类号： F01D5/20 , F01D5/186 , F05D2260/202
摘要： A blade for a gas turbine includes a tip cap and a tip squealer and passages for cooling fluid extending from a hollow space to the tip squealer. The tip squealer includes a cavity extending from the tip pocket into the tip squealer such that the cooling passage is divided into first and second portions with an exit hole in the cavity and an exit hole on the tip crown, respectively. In case of a blockage of the exit hole on the tip crown, cooling fluid can flow through the additional exit hole into the tip pocket and cool the squealer.
摘要翻译：用于燃气轮机的叶片包括尖端盖和尖端尖叫器以及用于冷却从中空空间延伸到尖端尖叫器的流体的通道。尖端尖叫器包括从尖端口延伸到尖端尖叫器中的空腔，使得冷却通道分别分成第一和第二部分，其中空腔中具有出口孔和顶端冠部上的出口孔。在顶端顶盖上的出口孔堵塞的情况下，冷却流体可以通过附加的出口孔流入尖端口并冷却鸣叫器。

5. 发明授权

US06634858B2 Gas turbine airfoil 有权
标题翻译：燃气轮机翼型
公开(公告)号：US06634858B2
公开(公告)日：2003-10-21
申请号：US09877073
申请日：2001-06-11
申请人： Norman Roeloffs , Samuel Miller
发明人： Norman Roeloffs , Samuel Miller
IPC分类号： F01D518
CPC分类号： F01D5/20 , B23P2700/06 , F01D5/186 , F01D5/187 , F05D2230/21 , F05D2260/202 , F05D2260/22141 , Y10T29/49341
摘要： An airfoil includes internal cooling air passages arranged in a serpentine manner with one or more radially outward and radially inward extending passages. The passages are in fluid connection through turns of approximately 180°. The turns near the platform of the airfoil connecting a radially inward extending passage with a radially outward extending passage are realized by a root turn defined by the passage sidewalls, which extend radially inward to the radially inner end of the root section of the airfoil, and by an end plate attached to the radially inner ends of the walls.
摘要翻译：翼型件包括以蛇形方式布置的内部冷却空气通道，其具有一个或多个径向向外和径向向内延伸的通道。这些通道通过大约180°的转动流体连接。通过连接径向向内延伸的通道和径向向外延伸的通道的翼型平台附近的转弯通过由径向向内延伸到翼型的根部的径向内端的通道侧壁限定的根部转弯实现，以及通过连接到壁的径向内端的端板。

6. 发明申请

US20060269419A1 Turbine blade trailing edge construction 有权
标题翻译：涡轮叶片后缘施工
公开(公告)号：US20060269419A1
公开(公告)日：2006-11-30
申请号：US11140631
申请日：2005-05-27
申请人： James Downs , Norman Roeloffs , Edward Pietraszkiewicz
发明人： James Downs , Norman Roeloffs , Edward Pietraszkiewicz
IPC分类号： B64C11/16
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/126 , F05D2240/304 , F05D2250/711 , F05D2250/712
摘要： A turbine blade system for a gas turbine engine includes a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge. The trailing edge region includes a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge. The trailing edge region defines a plurality of ejection slots each laterally disposed between two of the riblets. The plurality of riblets each define an upper surface having at least a portion in the lengthwise direction being curved relative to the pressure side surface so as to generally shield the upper surface from a high heat load propagating from the pressure side surface and to facilitate cooling air flowing from the ejection slots to flow over the upper surface.
摘要翻译：一种用于燃气涡轮发动机的涡轮机叶片系统包括涡轮叶片，其具有在侧向方向上延伸的后缘区域以及从压力侧表面到后缘的长度方向。后缘区域包括从压力侧表面向后缘沿长度方向延伸的多个肋条。后缘区域限定多个排出槽，每个排出槽横向设置在两个肋之间。多个肋条每个限定上表面，其具有相对于压力侧表面弯曲的长度方向上的至少一部分，以便将上表面大致屏蔽从压力侧表面传播的高热负荷，并促进冷却空气从喷射槽流出以流过上表面。

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