A turbomachine component, particularly a gas turbine engine component with a cooled wall and a method of manufacturing the same

The invention is directed to a turbomachine component (10), particularly a gas turbine engine component, comprising at least one part (2) built in parts from a curved or planar panel (11), particularly a sheet metal. The part (2) comprises a plurality of cooling channels (3) via which a cooling fluid (5), particularly air, is guidable, wherein at least one of the plurality of cooling channels (3) has a continuously tapered section (8). The at least one of the plurality of cooling channels (3) has a single inlet port (1) from a first surface (15) of the panel (11) and a single outlet port (7) for the cooling fluid (5) to another surface (16), particularly a surface opposite to the first surface (15), or to the first surface (15). Further the panel (11) is built via laser sintering or laser melting or direct laser deposition. The invention furthermore is directed to a gas turbine engine equipped with the component and a method of manufacturing the same. 本发明致力于种涡轮机组件(10)，具体为种燃气涡轮发动机组件，包括内置在来自弯曲或平面面板(11)，具体为金属薄片的