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1. 发明授权

US6068445A Cooling system for the leading-edge region of a hollow gas-turbine blade 失效
标题翻译：中空燃气轮机叶片前缘区域的冷却系统
公开(公告)号：US6068445A
公开(公告)日：2000-05-30
申请号：US111706
申请日：1998-07-08
申请人： Alexander Beeck , Bruce Johnson , Bernhard Weigand , Pey-Shey Wu
发明人： Alexander Beeck , Bruce Johnson , Bernhard Weigand , Pey-Shey Wu
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/22141
摘要： In a cooling system for the leading-edge region of a hollow gas-turbine blade, a duct (3), through which flow occurs longitudinally, extends from the blade root up to the blade tip and is defined in the region of the blade body (4) by the inner walls of the leading edge (5), the suction side (6) and the pressure side (7) and by a web (8). The inner walls of the suction side and the pressure side are provided with a plurality of ribs (9), which run slantwise and at least approximately in parallel. The suction-side ribs and the pressure-side ribs are offset from one another over the blade height. The ribs (9) run radially inward from the web (8) in the direction of the leading edge (5), merge into the radial in the region of the leading edge and are led around the leading edge. The deviation of the ribs (9) from the slant into the radial is effected with the smallest possible radius. The ratio of the height (h) of the ribs (9) to the local height (H) of the duct (3) is constant over the longitudinal extent of the ribs.
摘要翻译：在用于中空燃气涡轮机叶片的前缘区域的冷却系统中，纵向发生流动的管道（3）从叶片根部向上延伸到叶片尖端并限定在叶片体的区域（5）的内壁，吸力侧（6）和压力侧（7）以及腹板（8）之间。吸入侧和压力侧的内壁设置有多个倾斜且至少大致平行的肋（9）。吸力侧肋和压力侧肋在刀片高度上彼此偏移。沿着前缘（5）的方向从腹板（8）径向向内延伸的肋（9）在前缘的区域中合并成径向，并且围绕前缘引导。肋（9）从斜面到径向的偏差以尽可能小的半径进行。肋（9）的高度（h）与管道（3）的局部高度（H）的比率在肋的纵向范围内是恒定的。

2. 发明授权

US5919031A Coolable blade 失效
标题翻译：可冷却刀片
公开(公告)号：US5919031A
公开(公告)日：1999-07-06
申请号：US897765
申请日：1997-07-21
申请人： Kenneth Hall , Bruce Johnson , Bernhard Weigand , Pey-Shey Wu
发明人： Kenneth Hall , Bruce Johnson , Bernhard Weigand , Pey-Shey Wu
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/187 , F05D2260/2212
摘要： A coolable blade (10) essentially comprises a blade root (11) and a blade body (1), which is composed of a pressure-side wall (6) and a suction-side wall (5). They are connected to one another essentially via a trailing-edge region (4) and a leading-edge region (3) in such a way that at least one hollow space (2) used as a cooling-fluid passage is formed, in which ribs (7) are arranged. At least one rib (7) is configured in such a way that it has an apex (9) and two legs (14, 15), the legs (14, 15) of the rib being bent at an acute angle (8) relative to a radial plane (13). It is especially advantageous to arrange these ribs in a hollow space of double triangular shape having acute-angled triangular points in the region of the leading edge and the trailing edge.
摘要翻译：可冷却叶片（10）基本上包括由压力侧壁（6）和吸力侧壁（5）组成的叶片根部（11）和叶片本体（1）。它们基本上通过后缘区域（4）和前缘区域（3）彼此连接，使得形成用作冷却流体通道的至少一个中空空间（2），其中排列肋（7）。至少一个肋（7）被构造成使得其具有顶点（9）和两个腿（14,15），所述肋的腿部（14,15）以相对于锐角（8）弯曲到径向平面（13）。将这些肋布置在具有在前缘和后缘的区域中具有锐角三角形点的双三角形形状的中空空间中是特别有利的。

3. 发明授权

US06056508A Cooling system for the trailing edge region of a hollow gas turbine blade 失效
标题翻译：用于中空燃气轮机叶片的后缘区域的冷却系统
公开(公告)号：US06056508A
公开(公告)日：2000-05-02
申请号：US111778
申请日：1998-07-08
申请人： Bruce Johnson , Pey-Shey Wu , Bernhard Weigand , Prith Harasgama
发明人： Bruce Johnson , Pey-Shey Wu , Bernhard Weigand , Prith Harasgama
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： In a cooling system for the trailing edge region of a hollow gas turbine blade, there extends from the blade root (1) to the blade tip (2) a duct (3) through which the flow passes longitudinally and which, in the region of the blade body (4), is delimited by the inner walls of the trailing edge (5), the suction side (6) and the pressure side (7) and by a web (9), the inner walls of the suction side and of the pressure side being provided with a plurality of ribs (8) running at least approximately parallel. The ribs (8) run obliquely from the web (9) in the direction of the trailing edge (5) and are directed radially outward on at least one of the two inner walls. The suction-side ribs and the pressure-side ribs are offset relative to one another over the blade height. The ratio of the height (h) of the ribs (8) to the local height (H) of the duct (4) is constant over the longitudinal extent of the ribs.
摘要翻译：在用于中空燃气涡轮叶片的后缘区域的冷却系统中，从叶片根部（1）延伸到叶片尖端（2），管道（3），流体沿纵向延伸通过该管道（3）叶片体（4）由后缘（5），吸力侧（6）和压力侧（7）的内壁和腹板（9），吸力侧的内壁和的压力侧设置有至少大致平行的多个肋（8）。肋（8）沿着后缘（5）的方向从腹板（9）倾斜延伸并且在两个内壁中的至少一个上径向向外指向。吸力侧肋和压力侧肋在叶片高度上相对于彼此偏移。肋（8）的高度（h）与管道（4）的局部高度（H）的比例在肋的纵向范围内是恒定的。

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