| 发明名称 | Turbine of a turbomachine | ||
| 摘要 | A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow. | ||
| 申请公布号 | US9255480(B2) | 申请公布日期 | 2016.02.09 |
| 申请号 | US201113284068 | 申请日期 | 2011.10.28 |
| 申请人 | GENERAL ELECTRIC COMPANY | 发明人 | Smith Paul Kendall;Siden Gunnar Leif;Bielek Craig Allen;Vandeputte Thomas William |
| 分类号 | F01D5/14 | 主分类号 | F01D5/14 |
| 代理机构 | Dority & Manning, PA | 代理人 | Dority & Manning, PA |
| 主权项 | 1. A turbine of a turbomachine, comprising: opposing first and second endwalls defining a pathway for a fluid flow; and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway, the plurality of the blade stages including a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage, the plurality of the nozzle stages including a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage, and at least one of the next-to-last blade stage and the next-to-last nozzle stage including aerodynamic elements configured to interact with the fluid flow and to define a throat distribution as a radial throat distribution that is a circumferentially averaged profile that exhibits a non-dimensional relative exit angle distribution ranging from between 1.00 and 1.05 at the first endwall to between 0.95 and 1.00 at the second endwall, wherein adjacent blades of the next-to-last blade stage are arranged such that the throat distribution increases along an entire span of the blades and adjacent nozzles of the next-to-last nozzle stage are arranged such that the throat distribution increases along an entire span of the nozzles. | ||
| 地址 | Schenectady NY US | ||