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1. 发明申请

US20120051900A1 TURBINE NOZZLE WITH CONTOURED BAND 有权
标题翻译：涡轮喷嘴带轮廓带
公开(公告)号：US20120051900A1
公开(公告)日：2012-03-01
申请号：US12872485
申请日：2010-08-31
申请人： Jeffery Donald Clements , Vidhu Shekhar Pandey , Ching-Pang Lee
发明人： Jeffery Donald Clements , Vidhu Shekhar Pandey , Ching-Pang Lee
IPC分类号： F01D1/02
CPC分类号： F01D9/02 , F01D9/04
摘要： A turbine nozzle includes an array of turbine vanes between inner and outer bands. Each vane includes opposed pressure and suction sides extending between opposed leading and trailing edges. The vanes define a plurality of flow passages each of which is bounded between the inner band, the outer band, and adjacent first and second vanes. A surface of the inner band in each of the passages is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of the first vane adjacent its leading edge, and a trough of relatively lower radial height is disposed parallel to and spaced-away from the suction side of the second vane aft of its leading edge. The peak and trough define cooperatively define an arcuate channel extending axially along the inner band between the first and second vanes.
摘要翻译：涡轮喷嘴包括在内带和外带之间的涡轮叶片阵列。每个叶片包括在相对的前缘和后缘之间延伸的相对的压力和吸力侧。叶片限定多个流动通道，每个流动通道限定在内带，外带和相邻的第一和第二叶片之间。每个通道中的内带表面的轮廓是非轴对称的形状，包括邻近第一叶片邻近其前缘的压力侧相对较高的径向高度的峰，并且设置相对较低径向高度的槽平行于其前缘的第二叶片后部的吸入侧并与其间隔开。峰和槽限定协同地限定沿着第一和第二叶片之间的内带轴向延伸的弓形通道。

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