Patent ID: 9255480
Filing Date: 2016-02-09
CPC Classification: F01D,F05D

Claim Text:
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.