Invention Grant
US07984607B2 Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity 有权
燃气轮机发动机系统和相关方法涉及叶片数比大于一

Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity
Abstract:
Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity are provided. In this regard, a representative turbine stage for a gas turbine engine includes a first set of rotatable blades operative to be positioned downstream of and adjacent to a first set of vanes, a number of blades of the first set of blades being less than a number of vanes of the first set of vanes.
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