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1. 发明授权

US06568187B1 Effusion cooled transition duct 有权
标题翻译：流出冷却过渡管
公开(公告)号：US06568187B1
公开(公告)日：2003-05-27
申请号：US09683290
申请日：2001-12-10
申请人： Stephen W. Jorgensen , James H. Leahy, Jr.
发明人： Stephen W. Jorgensen , James H. Leahy, Jr.
IPC分类号： F02C314
CPC分类号： F01D9/023 , F05D2260/202 , F23R2900/03041
摘要： An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet sleeve, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. Effusion cooling geometry, including coverage area, hole size, and surface angle will be optimized in the transition duct to tailor the temperature levels and gradients in order to minimize thermally induced stresses. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life.
摘要翻译：公开了一种用于将热气体从燃烧器传送到涡轮机的渗出冷却的过渡管道。过渡管道包括具有大致圆柱形的入口端和具有增加的第一和第二曲率半径的大致矩形出口端的面板组件，大致圆柱形的入口套筒和大致矩形的端部框架。过渡管道的冷却通过与过渡管道的端部框架成角度的多个孔相对于过渡管道的外壁以锐角钻出。在过渡管道中将优化包括覆盖面积，孔尺寸和表面角度在内的流出冷却几何，以调整温度水平和梯度，以最小化热致应力。面板组件的曲率半径的增加与渗出冷却孔的组合减少了部件应力并增加了部件的使用寿命。

2. 发明授权

US06640547B2 Effusion cooled transition duct with shaped cooling holes 有权
标题翻译：输出冷却过渡管道，带有形状的冷却孔
公开(公告)号：US06640547B2
公开(公告)日：2003-11-04
申请号：US10280173
申请日：2002-10-25
申请人： James H. Leahy, Jr.
发明人： James H. Leahy, Jr.
IPC分类号： F02C314
CPC分类号： F01D9/023 , F05D2260/202
摘要： An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet flange, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life. An alternate embodiment of the present invention is shown which discloses shaped angled holes for improving the film cooling effectiveness of effusion holes on a transition duct while reducing film blow off.
摘要翻译：公开了一种用于将热气体从燃烧器传送到涡轮机的渗出冷却的过渡管道。过渡管道包括具有大致圆柱形的入口端和具有增加的第一和第二曲率半径的大致矩形出口端的面板组件，大致圆柱形的入口凸缘和大致矩形的端框架。过渡管道的冷却通过与过渡管道的端部框架成角度的多个孔相对于过渡管道的外壁以锐角钻出。面板组件的曲率半径的增加与渗出冷却孔的组合减少了部件应力并增加了部件的使用寿命。示出了本发明的替代实施例，其中公开了用于在减少膜吹走的同时改善过渡管道上的渗出孔的膜冷却效果的成角度的孔。

3. 发明授权

US07104069B2 Apparatus and method for improving combustion stability 有权
标题翻译：提高燃烧稳定性的装置和方法
公开(公告)号：US07104069B2
公开(公告)日：2006-09-12
申请号：US10603208
申请日：2003-06-25
申请人： Vincent C. Martling , James H. Leahy, Jr.
发明人： Vincent C. Martling , James H. Leahy, Jr.
IPC分类号： F02C3/30 , F23R3/36
CPC分类号： F23D17/002 , F23D2204/10 , F23L7/005 , F23L2900/07009 , F23R3/36
摘要： A fuel nozzle for use in a gas turbine combustor is provided having the capability of injecting multiple fuel types as well as steam for NOx reduction. Combustion dynamics within a combustor due to the mal-distribution of steam are controlled by the placement of a meterplate at the steam inlet, such that the meterplate reduces steam velocity and increases steam pressure drop. A higher pressure drop reduces the sensitivity of the combustion process to upstream steam supply variations. A method for providing uniform steam flow to a plurality of fuel nozzle assemblies about a gas turbine engine is also disclosed.
摘要翻译：提供了一种用于燃气轮机燃烧器的燃料喷嘴，其具有喷射多种燃料类型以及用于NOx还原的蒸汽的能力。由于蒸汽的不均匀分布，燃烧器内的燃烧动力学通过在蒸汽入口处放置测量仪进行控制，使得仪表降低蒸汽速度并增加蒸汽压降。更高的压降降低了燃烧过程对上游蒸汽供应变化的敏感性。还公开了一种用于向围绕燃气涡轮发动机的多个燃料喷嘴组件提供均匀蒸汽流的方法。

4. 发明授权

US06705088B2 Advanced crossfire tube cooling scheme for gas turbine combustors 有权
标题翻译：燃气轮机燃烧器先进的交火管冷却方案
公开(公告)号：US06705088B2
公开(公告)日：2004-03-16
申请号：US10116850
申请日：2002-04-05
申请人： Vincent C. Martling , James H. Leahy, Jr. , Daniel J. Sullivan
发明人： Vincent C. Martling , James H. Leahy, Jr. , Daniel J. Sullivan
IPC分类号： F02C720
CPC分类号： F23R3/48
摘要： A crossfire tube assembly with telescoping inner and outer crossfire tubes with an enhanced cooling mechanism for connecting adjacent combustors in a gas turbine is disclosed. The enhanced cooling configuration includes a plurality of channels formed in the telescoping region of the inner and outer crossfire tubes of the assembly to improve heat transfer and reduce local operating temperatures such that component life is extended.
摘要翻译：公开了一种具有伸缩式内外交叉管的交火管组件，其具有用于连接燃气轮机中的相邻燃烧器的增强的冷却机构。增强的冷却配置包括形成在组件的内部和外部交叉火焰管的伸缩区域中的多个通道，以改善热传递并降低局部工作温度，使得部件寿命延长。

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