专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07467924B2 Turbine blade including revised platform 有权
标题翻译：涡轮叶片包括修订平台
公开(公告)号：US07467924B2
公开(公告)日：2008-12-23
申请号：US11205274
申请日：2005-08-16
申请人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
发明人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
IPC分类号： F01D5/10
CPC分类号： F01D5/3007 , F01D5/22 , F05D2230/31 , F05D2300/132
摘要： The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly from the airfoil and a root portion extending downwardly from the platform. Two suction side tabs extend a first distance outward from a suction side of the root potion. Two pressure side tabs extend outward from a pressure side of the root portion. One of the two pressure side tabs extends outward a distance similar to the first distance, however, the other of the two pressure side tabs extends outward a distance much smaller than the first distance, which reduces stresses acting on the turbine blade. In addition, a plurality of coatings are systematically applied to the turbine blade to further reduce mechanical stress factors and improve cooling.
摘要翻译：本发明提供一种涡轮叶片，其具有经修改的平台外结构，其包括独特的涂层组合，其减小涡轮叶片内的机械应力因素。涡轮叶片包括具有从翼型件向上延伸的翼型件和从该平台向下延伸的根部的平台。两个吸力侧翼片从根部的吸力侧向外延伸第一距离。两个压力侧翼片从根部的压力侧向外延伸。两个压力侧翼片之一向外延伸一段类似于第一距离的距离，然而，两个压力侧翼片中的另一个突出部向外延伸远远小于第一距离，这减小了作用在涡轮叶片上的应力。另外，将多个涂层系统地施加到涡轮叶片上，以进一步减少机械应力因素并改善冷却。

2. 发明授权

US07310588B2 System and method for verifying the dimensions of airfoils 有权
标题翻译：用于验证翼型尺寸的系统和方法
公开(公告)号：US07310588B2
公开(公告)日：2007-12-18
申请号：US11257433
申请日：2005-10-24
申请人： Karl A. Mentz , Bryan P. Dube , Richard M. Salzillo, Jr.
发明人： Karl A. Mentz , Bryan P. Dube , Richard M. Salzillo, Jr.
IPC分类号： G01B5/00
CPC分类号： G01B21/20 , G05B19/401 , G05B19/4184 , G05B2219/35128 , Y02P90/14 , Y10T29/49771
摘要： A computer-implemented method for verifying geometries of airfoils includes the steps of providing a part having an airfoil having an intended positional geometry and an intended feature geometry; measuring a first set of points of a primary datum system; determining an actual positional geometry of the airfoil based on the primary datum system measurements; calculating a first deviation between the intended positional geometry and the actual positional geometry of the airfoil; measuring a plurality of sets of points of at least one secondary datum system; determining an actual feature geometry of the airfoil based on the at least one secondary datum system measurement; calculating a second deviation between the intended feature geometry and the actual feature geometry of the airfoil; and performing a verification of the intended positional geometry and the intended feature geometry of the airfoil based upon the first deviation and the second deviation.
摘要翻译：用于验证翼型的几何形状的计算机实现的方法包括以下步骤：提供具有具有预期位置几何形状和预期特征几何形状的翼型的部件; 测量主基准系统的第一组点; 基于主基准系统测量确定翼型件的实际位置几何; 计算预期的位置几何形状和翼型件的实际位置几何之间的第一偏差; 测量至少一个次级数据系统的多组点; 基于所述至少一个次基准系统测量来确定所述翼型件的实际特征几何形状; 计算预期特征几何形状和翼型件的实际特征几何形状之间的第二偏差; 并且基于第一偏差和第二偏差来执行机翼的预期位置几何形状和预期特征几何形状的验证。

3. 发明授权

US07452186B2 Turbine blade including revised trailing edge cooling 有权
标题翻译：涡轮叶片包括修正后缘冷却
公开(公告)号：US07452186B2
公开(公告)日：2008-11-18
申请号：US11205299
申请日：2005-08-16
申请人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
发明人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： The present invention provides an improved cooling circuit for a trailing edge of a turbine blade. The cooling circuit includes an inlet passage that receives a airflow and distributes the airflow through a feed passage. The feed passage primarily includes trip strips, at least one barrier including cross-over holes, teardrop shaped protrusions, and pockets disposed along a trailing edge. The geometry and positioning of both the cross-over holes and teardrop shaped protrusions downstream of the cross-over holes have been optimized to maximize cooling efficiency and reduce airflow. An improved transition between the inlet passage and the feed passage is also provided, which is arcuate and allows the airflow to maintain attachment and flow unimpeded from the inlet passage to the feed passage. The geometry of the pockets disposed along the trailing edge is optimized to improve cooling.
摘要翻译：本发明提供了一种用于涡轮叶片的后缘的改进的冷却回路。冷却回路包括入口通道，其接收气流并将气流分配通过进料通道。进料通道主要包括跳闸带，至少一个屏障，包括交叉孔，泪珠形突起和沿后缘设置的凹穴。交叉孔下游的交叉孔和泪滴形突起的几何形状和定位已被优化，以最大化冷却效率并减少气流。还提供了入口通道和进料通道之间的改进的过渡，其是弧形的并且允许气流保持附件和流动从入口通道畅通到进给通道。沿着后缘设置的凹穴的几何形状被优化以改善冷却。

4. 发明授权

US07549846B2 Turbine blades 有权
标题翻译：涡轮叶片
公开(公告)号：US07549846B2
公开(公告)日：2009-06-23
申请号：US11197152
申请日：2005-08-03
申请人： Bryan P. Dube , John W. Golan , Randall J. Butcher , Richard M. Salzillo
发明人： Bryan P. Dube , John W. Golan , Randall J. Butcher , Richard M. Salzillo
IPC分类号： F01D5/14
CPC分类号： F01D5/3007 , F01D5/147 , F05D2230/10 , F05D2230/90 , F05D2240/80 , F05D2250/70 , F05D2250/71 , F05D2260/941
摘要： A turbine blade is provided for use in a gas turbine engine. The turbine blade has a platform, an airfoil radially extending from the platform, and an attachment portion comprising an asymmetric root neck portion having a higher stress side and a lower stress side. The turbine blade may further have additional material and a compound fillet for dispersing strain in a region where the airfoil overhangs the neck portion.
摘要翻译：涡轮叶片被提供用于燃气涡轮发动机。涡轮叶片具有平台，从平台径向延伸的翼型件以及包括具有较高应力侧和较低应力侧的不对称根部颈部的附接部分。涡轮机叶片可以进一步具有附加材料和复合圆角，用于在机翼突出到颈部的区域中分散应变。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式