发明名称 Gas turbine engine end-wall component
摘要 An end-wall component (26, 29) of the mainstream gas annulus of a gas turbine engine is provided. The component has a cooling arrangement including one or more circumferentially extending rows of ballistic cooling holes (33) through which, in use, dilution cooling air is jetted into the mainstream gas to reduce the mainstream gas temperature adjacent the end-wall. A portion of the cooling holes are first cooling holes angled such that the direction of the dilution cooling air jetted therethrough has, on entry into the mainstream gas annulus, a component in one tangential direction. A portion of the cooling holes are second cooling holes angled such that the direction of the dilution cooling air jetted therethrough has, on entry into the mainstream gas annulus, a component in the opposite tangential direction. The first and second cooling holes are arranged such that the cooling air from jets having entry components in opposing tangential directions collide and coalesce.
申请公布号 GB201219731(D0) 申请公布日期 2012.12.12
申请号 GB20120019731 申请日期 2012.11.02
申请人 ROLLS-ROYCE PLC 发明人
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