-
公开(公告)号：US08718989B2
公开(公告)日：2014-05-06
申请号：US11429954
申请日：2006-05-09
IPC分类号： G06F17/50
摘要： In a non-destructive method for determining the internal structure of a heat conducting body, such as a cooling structure of a turbine blade, a flow medium is passed through the internal structure and the resultant thermal image on an external surface of the body is registered using a pixelised thermal image detector. Heat transfer coefficients and wall thicknesses of the internal structure are determined by means of a 1-,2-, or 3-dimensional inverse method that includes the numerical modelling of the surface temperatures using initial values for heat transfer coefficients and wall thicknesses and an optimization of the values using an iteration method. In a special variant of the method, the spatial geometry of the internal structure of the body is determined by means of the same inverse method and a geometry model that is optimised by iteration. No prior knowledge of the internal geometry is required.
摘要翻译： 在用于确定诸如涡轮叶片的冷却结构的导热体的内部结构的非破坏性方法中，使流动介质通过内部结构，并且在身体的外表面上记录所得的热图像 使用像素化热图像检测器。 内部结构的传热系数和壁厚通过1，2或3维逆方法确定，其中包括使用传热系数和壁厚的初始值的表面温度的数值模拟和优化 的值使用迭代方法。 在该方法的特殊变型中，通过相同的逆方法和通过迭代优化的几何模型来确定身体的内部结构的空间几何。 不需要内部几何的先验知识。
-
公开(公告)号：US20060256837A1
公开(公告)日：2006-11-16
申请号：US11429954
申请日：2006-05-09
IPC分类号： G01K3/00
摘要： In a non-destructive method for determining the internal structure of a heat conducting body, such as a cooling structure of a turbine blade, a flow medium is passed through the internal structure and the resultant thermal image on an external surface of the body is registered using a pixelised thermal image detector. Heat transfer coefficients and wall thicknesses of the internal structure are determined by means of a 1-,2-, or 3-dimensional inverse method that includes the numerical modelling of the surface temperatures using initial values for heat transfer coefficients and wall thicknesses and an optimisation of the values using an iteration method. In a special variant of the method, the spatial geometry of the internal structure of the body is determined by means of the same inverse method and a geometry model that is optimised by iteration. No prior knowledge of the internal geometry is required.
摘要翻译： 在用于确定诸如涡轮叶片的冷却结构的导热体的内部结构的非破坏性方法中，使流动介质通过内部结构，并且在身体的外表面上记录所得的热图像 使用像素化热图像检测器。 内部结构的传热系数和壁厚通过1，2或3维逆方法确定，其中包括使用传热系数和壁厚的初始值的表面温度的数值模拟和优化 的值使用迭代方法。 在该方法的特殊变型中，通过相同的逆方法和通过迭代优化的几何模型来确定身体的内部结构的空间几何。 不需要内部几何的先验知识。
-
公开(公告)号：US08801371B2
公开(公告)日：2014-08-12
申请号：US13116523
申请日：2011-05-26
IPC分类号： F01D5/20
CPC分类号： F01D11/10 , F01D5/225 , F01D25/12 , F05D2260/2212 , F05D2260/22141
摘要： A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.
摘要翻译： 一种燃气轮机，包括具有带护罩和翅片的可旋转刀片的内壳和转子，以及布置在壳体中的空腔中并围绕可旋转叶片的冷却装置。 叶片护罩包括从叶片前缘延伸到空腔中的突起和用于冷却流体的空腔壁中的开口。 突起由相对于流动通道壁的角度限定。 突起影响通过开口进入的冷却流体的涡流和从流动通道进入空腔的热气体的涡流。 双涡流形成减少了冷却流与热气流的混合，并提高了叶片罩和空腔壁的冷却布置的效率。
-
公开(公告)号：US20110293402A1
公开(公告)日：2011-12-01
申请号：US13116523
申请日：2011-05-26
IPC分类号： F04D31/00
CPC分类号： F01D11/10 , F01D5/225 , F01D25/12 , F05D2260/2212 , F05D2260/22141
摘要： A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.
摘要翻译： 一种燃气轮机，包括具有带护罩和翅片的可旋转刀片的内壳和转子，以及布置在壳体中的空腔中并围绕可旋转叶片的冷却装置。 叶片护罩包括从叶片前缘延伸到空腔中的突起和用于冷却流体的空腔壁中的开口。 突起由相对于流动通道壁的角度限定。 突起影响通过开口进入的冷却流体的涡流和从流动通道进入空腔的热气体的涡流。 双涡流形成减少了冷却流与热气流的混合，并提高了叶片罩和空腔壁的冷却布置的效率。
-
公开(公告)号：US09464529B2
公开(公告)日：2016-10-11
申请号：US13245707
申请日：2011-09-26
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F05D2240/81 , F05D2260/202
摘要： A blade, for a gas turbine, includes a blade airfoil, having a shroud segment arranged on its upper end. The shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said shroud segment, on sides on which it adjoins adjacent shroud segments of the annular shroud, is provided with upwardly projecting side rails which extend along a side edge, to improve sealing to the hot gas passage. The side rails include rail-parallel or essentially rail-parallel, upwardly open slots through which cooling air, which is introduced via the shroud segment from an interior of the blade airfoil, discharges into the space above the shroud segment.
摘要翻译： 用于燃气轮机的叶片包括具有布置在其上端上的护罩段的叶片翼型件。 护罩部分与叶片排的其它叶片的护罩部分一起形成环形护罩，其限定燃气轮机的热气体通道，并且所述护罩段在其邻接环形护罩的相邻护罩段的侧面上设置有 向上突出的侧轨，其沿着侧边缘延伸，以改善对热气体通道的密封。 侧轨包括轨道平行或基本上轨道平行的向上开口的狭槽，经由护罩段从叶片翼型的内部引入的冷却空气通过该槽排放到护罩段上方的空间中。
-
-
-
-
搜索结果
5 条记录 (耗时 0.017 秒)
